rocketsat 8 preliminary design review
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2012CoDR
RocketSat 8 Preliminary Design
ReviewUniversity of Colorado
Boulder10/26/11
2012CoDR
Nomenclature
• RODEO – Roll Out De-Orbiting Device• VACA - Validation Assembly of
Communication Antennae• DONDE – Attitude Determination System
2
2012CoDR
Mission Statement
• To design a system that deploys the Roll Out De-Orbiting Device (RODEO) developed by Composite Technology Development (CTD). This shall provide a possible means to de-orbit future small satellites.
• To eject VACA for the examination of communication capabilities between two differently located antennas.
• To validate the Attitude Determination System (ADS) developed for RockSatC.
2012CoDR
Theory and Background
• The aerospace market has been continually moving towards small satellites
• Approximately 23 small satellites (10kg-500kg) are launched every year by the United States alone
• The continual growth of small satellites in space increases the likelihood of collisions exponentially
• The rise in number of satellites in orbit has led to an increasing need for a cost effective and lightweight means to de-orbit small satellites.
2012CoDR
Theory and Background Continued
• Communication distance and capability is often increased by having line of sight between a transmitter and receiver.
• DONDE was a small, low-cost system designed by RocketSat VII to determine the orientation of the payload through a CMOS optical sensor and other various devices.
5
2012CoDR
Mission Overview: Concept of Operations
Launch
Begin Telemetry
Splash Down
Apogee
Altitude: ≈160 kmDeploy RODEO
Deploy VACA
End of Orion Burn
Collect Data from VACA
Chute Deploys
Power off all systems
Pre-Launch
-G switch triggered
-All systems on
-Begin data collection
-Initialize Cameras
2012CoDR
Mission overview: Expected Results
• We expect that the RODEO system be extended whilst attached to the rocket
• We expect to capture images and video of the extended RODEO system
• We expect the VACA to be deployed from the main plate• We expect to measure signal quality between the
antennae • We expect the signal quality of the antenna on the
RODEO to be stronger than the one on the main plate• We expect to validate the attitude determined by
DONDE
2012CoDR
Main System Overview
8
2012CoDR
Main System Functions
• Houses other subsystems• Deploys RODEO• Validates RODEO • Ejects VACA• Processes Communication with VACA
2012CoDR
RequirementsProject Requirements
O1 Shall deploy the RODEO device Mission Objective
O2 Shall validate the deployment of the RODEO device Mission Objective
O3 Shall eject the VACA Device Mission Objective
O4 Shall validate that deployed antenna performs better than static antenna located on the main plate
Mission Objective
O5 Shall comply with all RockSat-X requirements Mission Objective
System Requirements
S1 Shall deploy the RODEO with an electro-mechanical release mechanism O1
S2 Shall capture image of deployed RODEO sail O2
S3 Shall eject VACA from the main plate through the use of deployment mechanism O3S4 Shall receive communications signals from VACA with both antennas and
compare signal strengthO4
S5 Shall meet all structural requirements as defined in the RockSat-X user guide O5S6 Shall meet all electrical requirements as defined in the RockSat-X user guide O5
2012CoDR
Requirements (cont.)
System Level 2 Requirements
S1.1 Shall deploy RODEO using an electromechanical actuator S1
S2.1 Shall deploy in a time sufficient for the needs of the mission S2
S2.1 Shall capture an images of RODEO while it is in the field of view of the camera S2
S2.2 Shall set a image frame rate and quality that confirms RODEO deployment S2
S2.3 Shall store the image data S2
S3.1 Shall detach from rocket at the determined time S3
S3.2 Shall detach from rocket without damaging equipment S3
S3.3 Shall generate acceleration upon detachment S3
S4.1 Shall communicate with antenna at end of RODEO and S4
S6.1 Shall have sufficient power to perform all required operations S6
2012CoDR
Structures Overview
12
2012CoDR
BC
A
Basic Design Overview
13
Single middle plate design: the RODEO, the cube sat (VACA) and its ejection system are mounted on the bottom of the middle plate. The ADS and electronic boards will be on top of the middle plate incased in an air tight shell with a view port for the camera.
Front ViewA- air tight shellB- Cube Sat & ejection system
C- RODEOD- Camera
Bottom ViewB- Cube Sat & ejection system
C- RODEOD- Cameras
ED
C
B
Top View (without airtight shell)D- ADSE- electronics board
DD
D
2012CoDR
Design
2012CoDR
Structural Requirements
Structures Subsystem Requirements
D1 The structure shall be made of materials that can withstand temperatures of re-entry S5
D2 The structure shall fit into the 12 inch diameter, 11 inch tall volume S5
D3The structure shall be able to withstand at least 25 g's sustained and impulses of up to 50 g’s and remain intact S5
D4 The entire RockSat X payload shall weigh 30±1 lb (13.607 kg) S5
D5The payload shall be designed to have a center of gravity (CG) that lies within a 1x1 inch envelope on the x-y plane of the structure. S5
D6The payload shall be designed such that it integrates on top and on bottom of a middle plate mounting system inside of the rocket. S5
D7 The structure shall insure that all electrical connections are secure throughout the entire flight. S1.1
D8 The structure shall maintain the position of each of the sensors during flight S1.1
D9 The structure and sensors shall not impact the canister during the vibrations of flight S1.1
D10 The structure shall allow for the correct degree of view for the sun sensor S1.1
2012CoDR
Structural Requirements
Structures Subsystem Requirements
D11The structure shall integrate an ejection system that will eject the VACA Cube-Sat device given to us by Composite Technology Development. S5
D12 The ejection system shall not pre-maturely eject VACA or malfunction due to the forces of launch S5
D13The structure will mimic the RockSat C program by having an encasing over the attitude determination system S5
D14 The encasing over the ADS will be airtight and should keep all data intact through splashdown S5
2012CoDR
Trade Study for Stack Mounting
MaterialStructural Integrity
(.50)
Chances of Image Captured
(.30)
Cost (.10)
Machine-ability (.05)
Flight Heritage (.05) Total
Middle Mount 8 7 5 8 10 7.5
Bottom Mount 6 7 5 8 9 6.45
2012CoDR
Stack Mounting• It has been decided to use the middle mount offered by
Wallops.• A middle mount will separate the two systems into airtight
and open to space• Open air hardware will be interfaced to electronics boards
via a sealed electrical feedthrough• The mount will also make sure the deployable is not in the
field of view of the camera.• The top and bottom mounts either connect to the top or
bottom, not both.– This is due to other projects being on either side of our
stack
2012CoDR
Preliminary Mass Budget
Mass Estimation Unit Weight (specified) Mass (lbs.)
Computer Boards na 1
Sensors 0.02425 lbs. 0.02425 lb
Sensor Enclosure .347 lb .347 lb
Middle Aluminum Plate .098 lb/in3 2.77088 lb
Makrolon Plate .043 lb/in3 .6838851 lb
ADS Canister .098 lb/in3 3.70413 lb
RODEO na ~ .25 lb
VACA na ~ 1 lb
Standoffs, other hardware na .5 lbs
Total na ~ 10.2801 lb
2012CoDR
Preliminary Testing
• Thermal analysis on metal components will be done to ensure hardware is safe upon reentry.
• SolidWorks Analysis– Our SolidWorks model will undergo structural testing in the SolidWorks
program.– SimulationXpress analysis will be used for load testing as well as
testing the torque of the design– This will also be used to determine the precise locations of sensors for
the best field of view. – Stress analysis in SolidWorks will show how forces on our model will be
distributed.
2012CoDR
Risk Analysis for Structural Failiures
5 Structure collapses
Failure to photograph deployment
4 Standoffs failEjection system failure
Risk 3 Plates crack
Sensor becomes detached from plate
Sail collapses after
deployment
2 Sensors become
misaligned
1
1 2 3 4 5
Probability
2012CoDR
Current Progress and Goals
Current Progress• Current design in SolidWorks of the main plate.• Research and decide type of ejection system (spring).Goals• Complete Solidworks stress analysis on each of our plate materials• Complete torque testing on the stack• Complete torque spec for materials to be used• Identify points of failure for mechanical model• Complete thermal analysis at reentry and electronics protection• Make more detailed designs in relation to updated system requirements• Researching materials to be implemented for stack• Assessing materials and parts to be ordered
2012CoDR
Electrical System Overview
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2012CoDR
Functions
• Deploy RODEO using timed event• Image RODEO with HD and low resolution
cameras• Communicate with VACA using RF• Process images and data• Store images, and data in on-board memory• Send data and low resolution images through
telemetry lines
2012CoDR
RODEO Electrical System
MCU
RF chip
Antenna 1
RODEO release Antenna 2
Power Converters
Memory
HD Camera
Lo-Res Camera
FPGA
from RockSatpower
totelem
toCubeSat
RFComm
Imaging
2012CoDR
Main System Power
• Power for the main plate shall be delivered by 28 V lines from the rocket
• Total power consumption for the mission shall not exceed the limit of 1 A/hr
• 28 Volt power shall be reduced to 9 Volt power for distribution to subsystems
• Filtering techniques shall be employed to reduce noise on power lines for reduction of errors in signal transmission
2012CoDR
Power Distribution Diagram
Buck Converter
ADS Main System MCU COMM
RODEO
28V
Linear Regulators
9V
2012CoDR
Main Power Requirements
Subsystem Voltage Current PowerMain MCU 3.3 V 18 mA .0594 W
ADS 9V .55 A 5 W
RODEO <9V <50 mA .45W
VACA n/a n/a Self Powered
COMM 3.3 V 215 mA .7095 W
Total Power Required from 28V lines ≈ 6.22 W
2012CoDR
DC to DC Conversion
• 28V power will be reduced to 9V power through the use of switched mode converter for decreased power losses
• DC conversion for microcontroller and other electronics components will be performed using linear regulators
Type RF Noise (20%)
Cost(20%)
Reliability(20%)
integration factor(10%)
power capabilitie
s(10%)
electrical noise(10%)
efficiency(10%)
Weighted Average
Buck 4 3 5 5 5 4 4 4.2
Boost 2 3 5 5 5 3 3 3.6
Buck-Boost 2 3 5 5 5 2 3 3.5
Split-pi 1 1 5 5 5 4 5 3.3
2012CoDR
Electrical Component Selection
30
• We will be selecting components to use in the electrical system based on performance requirements and ease of interface with other components.
• Primary hardware considerations:– Low power consumption– Accommodate interface protocols employed– Withstand launch, reentry conditions
2012CoDR
Electrical Component Selection
Microcontroller• Requirements:
– Interface with RF Comm System– Process data (sent via RF Comm)– Store data to memory– Upload data to telemetry lines
2012CoDR
Electrical Component Selection
• We chose the XMEGA256A3 microprocessor.– Same one used on last year’s system: driver software
already written, tested, and proven– Capable of interfacing with XBEE RF protocol
2012CoDR
Electrical Component Selection
Memory• Requirements:
– Non-volatile storage– Sufficiently fast write speed– Easily interfaced to microcontroller– Heat, vibrations resistent
2012CoDR
Electrical Component Selection
• We decided to use digital (SD) cards– Cheap, compact, reliable data storage– Non-volatile– Many available software libraries– Light-weight and durable
2012CoDR
Electrical Component Selection
Cameras:• Provide visual confirmation of RODEO deploy• One low-resolution camera
– Images processed on-board, sent to telemetry lines– Same camera as in VACA
• One high-resolution camera– Data saved straight to internal memory card– Hardware implementation: GoPro HD Hero2
Outdoor Edition
2012CoDR
Electrical Component Selection
HD Video Camera Resolution(Pixels) 30%
Frames per Second (fps) 25%
Angle of View 20%
Power 15%
Cost 10%
Weighted Average
1. ContourROAM 5 4 3 5 4 4.251. Go Pro HD Hero2
Outdoor Edition5 5 5 5 5 5
1. Oregon Scientific ATC9K
5 5 4 5 3 4.6
1. Drift HD170 5 5 3 5 2 4.3
HD Camera Selection:
2012CoDR
System Software Overview
37
2012CoDR
Software Overview
• Software for the main microcontroller will control all other non-deployable components of the main system
• Software will run efficiently and at a speed that will record and store all data
• Software will be programed as a state machine• Software will be redundant in order to prevent failures
moving from state to state• Redundancies include watchdog timers and secondary
signaling hardware to confirm timed events
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2012CoDR
Main Plate State Diagram
Off-Check State
Pre-Launch-Power Main MCU-Signal HD Camera-Signal ADS MCU-Power Low Res Camera-Start transmitting data through telem lines
Launch-Start Watchdog Timer
Deploy-Initialize mechatronics to deploy VACA
Apogee-Signal VACA-Deploy RODEO
Power Failure
User Power
Timed Event/G Switch
Timed Event/Watchdog Timer
Watchdog Time/Timed Event
2012CoDR
Language Trade Study
Language Speed(30%)
Efficiency(30%)
Versatility(20%)
Ease of Use
(10%)
Existing Code (10%)
Weighted Total
C 5 5 5 4 5 4.9
C++ 4 4 5 4 0 3.8
Assembly 4 4 2 1 0 2.9
2012CoDR
Software Concerns
• How to design the code for power failure survival • How to check the health system of the payload throughout
mission• How to mange component level failures• How to make code more robust and redundant • How to best integrate software functionality with hardware
41
2012CoDR
Subsystem A: RODEO
42
Courtesy of CTD
2012CoDR
Subsystem: RODEO
• RODEO is a drag inducing deployable boom developed by CTD for the deorbit of small satellites
• System shall electromechanically deploy RODEO device and validate deployment with deployment sensors and photo evidence
• HD video of the RODEO device will be recorded • A low resolution camera will capture images of the RODEO device and
transmit data to ground via the telemetry lines• The RODEO boom shall additionally house an antenna to increase
communication quality with VACA
2012CoDR
Structures: RODEO
• Rodeo shall be securely held in place on the bottom of the middle mount plate
• Rodeo will be mounted at the edge of the keep out zone so that sail deploys outside of rocket
2012CoDR
Structures: RODEO
Undeployed RODEOTwo camera angles-one HD camera-one low resolution camera
Deployed RODEO-three foot sail when fully extended
2012CoDR
RODEO Release Mechanism
• The RODEO is stored under potential within an aluminum structure
• The RODEO is contained with hinged door• The release of the hinged door produces an
extension of the rodeo sail in less than 1 second
2012CoDR
RODEO Release Mechanism Continued• The release of the RODEO containment door
will be executed using an electro-mechanical device
• The electro-mechanical device will be have sufficient holding torque for launch survival
• Testing will be done to ensure survivability and properly timed release of RODEO
2012CoDR
Rodeo Release Mechanism Continued
Possible Release Mechanisms• Frangibolt• Linear Actuator• Burn Wire
Release Mechanism Characteristics• Launch survivability• Size and weight constraints• Ease of integration with RODEO• Ease of electrical interfacing• Cost
Courtesy of WikipediaCourtesy of Tiniaerospace
2012CoDR
RODEO Electrical Interface
49
• A timer-controller power line will switch to high voltage at the time that we will want the RODEO to deploy.
• The signal will trigger power to be sent to the release latch
2012CoDR
VACA
50
2012CoDR
Subsystem: VACA
• Ejected from main system via deployment mechanism
• Houses antenna that communicates with antenna on the main plate and at end of RODEO
• Serves as basis upon which to test locations effect on signal strength
• Sends collected data to the main system to be stored and analyzed later
2012CoDR
Structures: VACA
• The structure shall deploy the Cube-Sat (VACA) out of the rocket at apogee.
• The deployment system thus far will be composed of springs and tracks that will push out VACA squarely to the structure.
• The deployment shall not interfere with any other operations in progress.
2012CoDR
Trade Study for VACA Ejection System
MaterialOdds of Success
(.50)
Required Hardware
(.30)
Cost (.10)
Machine-ability (.05)
Flight Heritage (.05) Total
Springs 8 8 7 8 10 8
Compressed Air 2 6 6 8 2 3.9
Motor Driven 6 6 4 8 9 6.05
2012CoDR
Ejection System
• From the trade study a spring powered is the most logical option for powering the system.
• Compressed air cannot be easily flown with pressure differentials and safety in mind.
• The spring will need to be very well protected to avoid an accidental ejection therefore our release mechanism will provide sufficient holding stability.
2012CoDR
55
We are looking into options for the deployable mechanism that include a loaded spring and electronic releasing switch that will be triggered at the ideal time of release, and will be secure throughout the launch and flight.
- We are currently looking into software developed by Sierra Nevada that is meant to eject objects from rockets into a space environment. The one pictured is called a Hold Down Release Mechanism, and is characterized by low shock and reusability.
Other options include a frangibolt system and a linear actuator.
2012CoDR
Vaca Power Requirements
Component Voltage Current PowerXbee Transceiver 3.3 V 215 mA .7095 W
Sensors 3.3 V < 1 mA < 1 mW
Xmega Microcontroller
3.3 V 18 mA 54 mW
Power Source Options• Rechargeable Batteries• Nonrechargeable Batteries
• Alkaline Long Life• Nickel Cadmium• Nickel Metal Hydride
Power Conversion Options• Linear Regulator• Switch Mode Converters
2012CoDR
Vaca Power
• The VACA structure shall be powered separately from the main structure using 9 volt long life alkaline batteries
• Hardware voltage requirements will be met using linear regulators to reduce battery voltage
• Batteries shall provide sufficient power for all operational tasks of the VACA structure while meeting weight constraints
2012CoDR
CubeSat Electrical Subsystem
MCU
Power
Memory
RF Chip
AntennatoRODEO
Sensors
Temp
Mag
2012CoDR
VACA Hardware
• Same microcontroller and memory as main board: easiest RF interface with RODEO subsystem
• Temperature sensor and accelerometer provide data to be sent over RF Comm
2012CoDR
VACA State Diagram
OFF/PRE-APOGEE
VACA Operating
Signal Initia
tion
-Turn on VACA-Initialize sensors-Initialize comm -Begin transmitting all data
Power failure
2012CoDR
Subsystem: Communications
• Consists of antennae in BRONCO, on RODEO boom, and in VACA
• Measuring signal strength of these communications part of mission
2012CoDR
Communication
Communication between main payload and CUBESAT involves :
• Two antennas on the RODEO (one each on the base and tip)
• A transmitter on VACA
• VACA shall transmit data received from the sensors to the main payload.
• Data will be received through both the antennas on the main payload and compared to measure the quality of reception .
• All the received data will then be stored onboard and if possible sent through telemetry lines to the ground station.
2012CoDR
RF Communication Layout
RF Chip
AntennaRF chip
Antenna 1
Antenna 2
to Power to Power
to MCU
to MCU
CubeSatRODEO
2012CoDR
XBEE Overview
• Xbee is a low-cost, low-power over-the-counter radio communications system designed for easy short-range data transmission.
• It is available in various configurations to suit the user’s needs.
• It can be used for wireless point-to-point communication ranging from 30m to 24000m which should facilitate ample communication time.
• It supports data transfer rates up to 250kbps which is enough to transfer the sensor data from VACA to main payload.
2012CoDR
How Xbee works?• Xbee Modules interface with a host device like a microcontroller
through a logic-level asynchronous port.
• Through this serial port it can communicate with any logic and voltage compatible UART.
Source: XBEE Datasheet
2012CoDR
How does Xbee work?
XBee uses the IEEE 802.15.4 networking protocol:
• Clear Channel Assessment (CCA): Before transmitting it checks to see if the selected frequency is busy. • Addressing: It has both a fixed 64-bit serial number (MAC address) which may be used for addressing, or a 16-bit assignable address
• Error Checking and Acknowledgements: It uses a checksum to help ensure received data contains no errors. Acknowledgements are sent to the transmitting node to indicate proper reception.
2012CoDR
XBEE Specifications
XBEE Pro 900 U.FL Device:• 900 MHz operating frequency• 156 Kbps data rate• 6 mile range• -40 to 85 OC operational temperature• 3.3 V, 210 mA operating power
2012CoDR
Antenna Specifications
Description: This connector cable interfaces UFL RF connectors to RP-SMA antennas. It can be used to attach any standard RP-SMA 2.4GHz antenna to the DPAC 802.11 modules.Dimensions: 4" Length
Description: 2.4GHz Duck Antenna 2.2dBi with Reverse Polarized - SMA RF connector. 50 ohm impedance. Dimensions: 4" Length
2012CoDR
DONDE
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2012CoDR
Subsystem: DONDE
• Housed within BRONCO• Consists of modified ADS from last year• Employs an optical CMOS and magnetometer to
obtain two absolute vectors as well as gyroscopes to update the payloads position
2012CoDR
Structures: DONDE
• This year we are re-designing the ADS to become smaller and more efficient.
• Structurally it will be shorter and designed so that the electronics board can be mounted horizontally.
• It is also being designed so that the camera will be on a separate board standing vertically in the bracket shown
2012CoDR
Structures: ACC
• The Airtight Covering Canister is a protective incasing that will cover all of the electronics boards and the ADS
• The canister will have a viewport so that the ADS can see into the space environment, as well as a conical object that will go from the viewport to the lens on the ADS
2012CoDR
Structures: ACC
Cone which blocks all reflection from camera to viewport
Mimic of RockSat C viewport
ACC Canister
ADS
Middle Plate
New Field of View
RocketSat VII Field of View
Camera Lens
2012CoDR
Attitude Determination System
Functions• Receives data from sensors• Processes and stores data in on-board memory• Upon, payload retrieval, data will be processed to
create attitude profile for flight
2012CoDR
DONDE Electrical System Schematic
MCUXMEGA256A3
Gyroscope
MagnetometerHoneywell HMC5883L
CameraToshiba TCM 8230 MD
MemorySD card
FPGA
Power In
2012CoDR
Modifications on Previous ADS
• Use of an FPGA for the low resolution camera instead of the CPLD increases the efficiency of the ADS
• FPGAs have a better processing speed than CPLDs.
• Camera can be more fully utilized .• Reduces complexity and footprint optical
circuitry.
• Use power from wallops instead of 9V batteries.• Cheaper, no weight penalty, more reliable.
2012CoDR
DONDE Hardware
Microcontroller• Requirements:
– Collect data from magnetometer, gyroscopes.– Supply these sensors with operation power.– Format sensor data.– Save sensor data to on-board memory.
• Most probable hardware implementation: XMEGA256D3 (same as last year)
2012CoDR
A
Vector determination methods:
Sensor Vector Producedsun position absolute
magnetometer absolute
gyroscope relative
DONDE Hardware
2012CoDR
Camera:• Activated by microcontroller• Takes pictures out payload opening• Pictures sent to FPGA to be processed• Processed data saved straight to memory card
from FPGA• Same hardware as in previous version: Toshiba
TCM8230MD (A)
DONDE Hardware
2012CoDR
ADS: Risk Matrix
80
Consequence
Magnetometer Failure
Gyroscope Failure
Sun Sensor Failure
Possibility
2012CoDR
DONDE State Diagram
OFF STATE
OPERATING STATE
Receive SignalMain MCUInitialize all
Devices-CMOS Camera-Gyroscopes-MagnetometersBegin Storing all Data
Power Failure
2012CoDR
Project ManagementAndrew Broucek
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2012CoDR
Organizational Chart
83
Andrew BroucekProject Manager
Wheeler GansSystems Lead
Nate Keyek-Franssen
Structures Lead
Emma YoungScience Lead
Andrew ThomasElectrical Lead
Ethan LongSoftware Lead
Devin MackenzieStructures
Kameron MedinaStructures
Eric LobatoScience
Aram PodolskiScience
Shreyank AmartyaElectrical
Brendan LeeElectrical
Long TatSoftware
Shawn CarrollProgram Manager
Mentor from CTDPhil Keller
Lia MatthewsAdvisor (COSGC)
2012CoDR
Schedule: First Semester
84
Task Start Date Completion Date
Preliminary Design Review - Oct 27
Software: ADS code Oct 27 Nov 15
Science/Electrical: 2 Antennae 1transmitter project Oct 27 Nov 9
Software: HD Camera & Low Res. Camera Outline Nov 15 Nov 25
Electrical: Hardware mapped out Oct 30 Nov 30
Electrical/Software: Sending images through telemetry Oct 30 Nov 30
Conceptual Design Review Nov 3 Nov 29
Software: Memory & Mechatronics Outline Nov 15 Nov 30
Software: Main MCU, VACA MCU, & COMM Outline Nov 20 Dec 5
Structures: Design completed (SolidWorks) Oct 30 Dec 5
Structures: Thermal analysis Nov 9 Dec 5
Order Hardware Dec 5 -
2012CoDR
Schedule: Second Semester
85
Task Start Date Completion Date
Electrical: 1st rev. Altium board designs & ordering Jan 1 Jan 30
Electrical: Fabrication of PCB’s (all revisions) Jan 1 Feb 15
Science: Testing Documentation Jan 1 Feb 25
Software: Testing code(all systems) Jan 1 March 9
Structures: Fabrication of structure Jan 1 March 9
Software: Flight Code March 9 April 13
VACA and COMM Integration & Testing March 9 March 16
RODEO Integration & Testing March 16 March 30
ADS Integration & Testing March 30 April 13
Full system checkout April 13 April 27
Launch Readiness Review - Jun 5
Testing and Environmental w/Wallops Jun 15 Jun 21
Launch! Jul 19 -
2012CoDR
Budget
86
Margin: 0.25 Budget:$5,000.00 Last Update:10/26/2011RocketSat 8
Item Supplier Estimated Cost Number Required Total Cost NotesStructures
Aluminum OnlineMetals $600.00 1 $600.00 Materials (nuts, bolts, etc.) mcmaster carr $200.00 1 $200.00 Misc. $100.00 1 $100.00 RODEO CTD $0.00 1 $0.00 Ejection System SNC $0.00 1 $0.00 Currently in the talks
Electrical/SoftwarePCB's Advanced Circuits $116.67 3 $350.01 3 board revisionsMicrocontrollers DigiKey $15.00 12 $180.00 Sensors (Cameras, gyros, magnetometer) DigiKey/SparkFun $200.00 1 $200.00 COMM DigiKey/ SparkFun $400.00 1 $400.00 ADCs, Regulators, etc. DigiKey $400.00 1 $400.00 Misc. $50.00 1 $50.00 HD Camera $300 1 $300.00
ScienceTesting Materials $300.00 1 $300.00 Misc. $100.00 1 $100.00
Total(no margin) $3,180.01 Total(with margin) $4,430.01
2012CoDR
Questions?
87
2012CoDR
References
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• http://www.tiniaerospace.com/ca/caimages/1cafc12.jpg\• http://upload.wikimedia.org/wikipedia/en/thumb/c/c3/Linear_ac
tuator_photo.jpg/220px-Linear_actuator_photo.jpg
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