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2012CoDR
RocketSat 8 Conceptual Design
ReviewUniversity of Colorado
Boulder10/4/11
2012CoDR
Mission Statements
• RocketSat 8 shall integrate and validate the Roll Out De-Orbiting Device (RODEO) developed by Composite Technology Development (CTD). This shall provide a means to de-orbit future small satellites.
• RocketSat 8 shall validate an attitude determination system for future RockSat missions
2012CoDR
Theory and Background
• 23 small satellites (10kg-500kg) launched every year by the United States
• Growth of small satellites in space exponentially increases the likelihood of collisions
• The rise in the number of satellites in orbit has led to an increasing need for a cost effective and lightweight means to de-orbit small satellites.
• The RocketSat VII attitude determination system was successful, but the accuracy of the system couldn’t be verified since there was no known solution for the attitude of the rocket.
2012CoDR
Requirements
Project Requirements Parent Requirement
O1 Shall deploy the RODEO device Mission Objective
O2 Shall validate the deployment of the RODEO device Mission Objective
O3 Shall validate the ability of RODEO to de-orbit small satellites
Mission Objective
O4 Shall comply with all RockSat-X requirements Mission Objective
O5 Shall determine the orientation of the payload Mission Objective
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Requirements (cont.)System Requirements Parent
RequirementS1 Shall deploy the RODEO device on the RTS (RODEO Test Structure) O1S2 Shall capture image of deployed RODEO sail O2S3 Shall detach the RTS from the rocket canister O3S4 Shall confirm that RTS experiences deceleration O3
S5 Shall meet all structural requirements as defined in the RockSat-X user guide
O4
S6 Shall meet all electrical requirements as defined in the RockSat-X user guide
O4
S7 Shall determine the orientation of the payload within ten degrees of accuracy
O5
S8 The orientation of the payload shall be known on all three axis O5
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Requirements (cont.)System Level 2 Requirements Parent
RequirementS1.1 Shall deploy in a time sufficient for the needs of the mission S1
S2.1 Shall capture an image 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 measure deceleration of the RTS S4
S4.2 Shall transmit deceleration data from RTS to the rocket S4
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Requirements (cont.)System Level 2 Requirements (continued) Parent
RequirementS6.1 Shall have sufficient power to perform all required operations S6
S7.1 Shall use attitude sensors that are within five degrees of accuracy
S7
S7.2 Shall incorporate an attitude determination algorithm that is accurate to within ten degrees of accuracy
S7
S8.1 Shall employ attitude sensors that can determine the attitude on all three axes
S8
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Minimum Success Criteria
• Mission success depends on the image capture of the deployed RODEO device.
• Secondary mission success is determined by the validation of the RocketSat8 attitude determination system
2012CoDR
Mission overview: Concept of Operations
Continue Telemetry
Splash Down
End TelemetryPre-Launch
-Begin Telemetry
-Begin attitude data collection
Deploy RTS
RTS data collection
Send Data from RTS to payload
Apogee
Altitude: ≈160 km
Initialize Camera
Begin Rodeo Deployment
Chute Deployment
Continue Telemetry
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Mission overview: Expected ResultsWe expect:• the RODEO system to be fully extended while attached to the
rocket
• to capture an image of the extended RODEO system
• the RTS to detatch from the rocket canister
• to measure deceleration from the RTS
• to transmit the deceleration data from the RTS
• We expect to characterize the rockets attitude and verify it with a known solution
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2012CoDR
Design Overview
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2012CoDR
User Guide Compliance: Structures
• The payload shall fit into the allotted 12 in diameter base and 11 in height and weigh less than 30 +- 1 lb.
• The center of gravity shall be within 1 square inch of the RockSat-X deck.
• Materials with a high resistance to stress corrosion and cracking, and a low outgassing index will be used.
• The deployable shall conform to all standards to safely eject from the canister.
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2012CoDR
Payload Layout: Structures
• The structure thus far will be composed of two plates.• The bottom plate will include the RTS containing the
deployable given to us by Composite Technology Development, as well as the ejection system.
• The electronics boards and the ADS(Attitude Determination System) will all be utilized on the top plate with the cameras.
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2012CoDR
Payload Layout: Structures
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Electronics BoardD
eplo
yabl
eBottom Plate
Camera onbottom of top plate
Top Plate
Keep Out Zone
Eje
ctio
n S
yste
m ADS
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RODEO Test Structure (RTS) Layout: rough diagram
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RTS
RODEO
Note: Drawing not drawn to scale
2012CoDR
Mission Requirements
• The payload shall conform to the requirements set forth in the 2011 RockSat-X User Guide
• The system shall successfully deploy the hardware manufactured by Composite Technology Development.
• The structure will interface with RockSat-X through provided mounting surfaces.
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Mission Requirements: Electronics Integration• All electronic interfaces will be held in place throughout the duration of
the flight with the exception of the deployable.
• The structure will withstand the forces of launch and protect the scientific and electrical systems.
• The structure will thermally protect the electronics for as long as reasonable data can be collected.
• The system shall successfully take at least one photo of the deployable as it leaves the canister, and house the cameras securely during launch.
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2012CoDR
Mission Requirements: Ejection System
• The ejection system shall be durable enough to survive the forces of launch.
• The structure shall allow exposure to an open air environment while still protecting electronics and instruments from harm.
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Electrical Subsystem
Electrical Subsystems:- Power- Memory- Radio Communications (Comm)- Mechatronics- Imaging
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Conceptual Electrical Configuration
Note: Not actual layout
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MCU
RTS Deploy
PowerComm
Mem
ory Power
Comm
Imaging
SailDeploy
MCU
Main Structure
RTS
Sensors
Power lineDigital lineAnalog Line
Charging(beforedeploy)
Radio
ADS
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User Guide Compliance: Electrical• The GSE Controlled power lines shall carry a total
current of less than 1.85 A.• The Timer Controlled power lines shall carry a total
current of less than 3.75 A.• All telemetry lines shall operate in the range of 0 – 5 V.• All components shall operate at 28 V or less. Higher
voltages shall be used only with express written permission.
• All components shall be conformal coated to protect from the space environment.
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State Chart: Software
State 1Pre-Launch
State 2Launch
State 3Apogee
State 4Post-Apogee
State 5Splash Down
Power On
G Switch
Initial Code• Initialize Devices• Check G Switch
No
Main Code• Store Data• Check Timed
Sequence One
Yes
TelemetryApogee Code
• Initialize Camera• Delay 30 seconds
CameraDeploy Code
• Deploy RTS• Get Data RTS
Yes
Telemetry
RTS
Final Code• Check Time
Sequence Two• Stop Recording
Telemetry
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Design Overview: RockSat-X 2012 User’s Guide Compliance
ComplianceRough Order of Magnitude (ROM) mass estimate
Plates and launcher ~ 10 lbsRts ~ 2-3 lbs
Estimate on payload dimensions RTS~ 1U cube sat configuration
Deployables/booms? Yes-Deployable
How many ADC lines? Exact amount not confirmed
Asynchronous use? Yes
Parallel use? Yes
Power lines and timer use? Yes- will need timer for RTS deployment
CG requirement UnderstoodAre you utilizing high voltage? No
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Management
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
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Preliminary Schedule- Important Dates
Task DateConceptual Design Review
(CoDR)10/4/11
Online Progress Report 1 Due
10/21/11
Preliminary design Review (PDR)
10/25/11
Online Progress Report 2 Due
11/11/11
Critical Design Review (CDR)
11/29/11
Order Hardware and Begin Fabrication
12/5/11
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Preliminary Schedule- Weekly Schedule
Day Time/DescriptionMonday 1-3pm Software Team meeting
Tuesday 2-3pm Structures Team meeting5-7pm Science Team meeting
Wednesday 2-3pm Executive Meeting
Thursday 4-6pm Electrical Team meeting
Mon-Fri 5-8pm Common working hours
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Budget
Source of Funding AmountComposite Technology Development $24,000
UROP (Not Confirmed) ~$3,000
EEF(Not Confirmed) ~$2,000
Total: $29,000
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Additional Support
• We will be working in conjunction with Composite Technology Development (CTD). Our main advisors from CTD are still to be determined
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Conclusions
Mission StatementTo integrate and validate the Roll Out De-Orbiting Device
(RODEO) developed by Composite Technology Development (CTD) and test the attitude determination system from
RocketSat VII Next Steps• Prepare for PDR• Finalize Design
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Questions
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Refrences1"The Bright Future of Small Satellite Technology :: Via Satellite." Guest Edition :: Satellite Today. Web. 04 Oct. 2011. <http://www.satellitetoday.com/via/features/37150.html>.
2Carroll, Shawn, and Chris Koehler. Rocksat-X User Guide. 8 Feb. 2011. PDF.
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