DINO PDR 23 October 2015 DINO Systems Team Jeff Parker Anthony Lowrey

DINO PDR 23 October 2015 Colorado Space Grant Consortium Big Picture Assure that DINO’s design meets all of DINO’s objectives DINO’s Mission Objectives: –DINO will demonstrate deployable structures for nanosatellites –DINO will demonstrate onboard intelligent operations –DINO will measure cloud heights from space using a stereoscopic imaging technique –DINO will provide educational support for K-12 and college-level students

DINO PDR 23 October 2015 Colorado Space Grant Consortium System Requirements The spacecraft system shall meet its Mission Objectives Requirements –Deployable objectives –Intelligent operations objectives –Science objectives –Education objectives The spacecraft system shall meet its Operational Requirements –Survive launch Launched in a Space Shuttle –Operate in space for 12 months –Two-way communication between the spacecraft and ground for the full mission duration –Full support from mission operation control center for mission duration

DINO PDR 23 October 2015 Colorado Space Grant Consortium System-Level Tasks Keep the entire system on-track Ensure that all deadlines are met Ensure proper communication –Between subsystems –With Industry/Academic supporters Ensure proper safety in each of DINO’s phases –Design, construction, integration, testing, transportation, and delivery Design, build, test all interfaces –Subsystem communication interfaces –Integration and test fixture –Ground support equipment Provide and manage all necessary documentation Support all subsystems

DINO PDR 23 October 2015 Colorado Space Grant Consortium System Tools Requirement Document –DINO’s Objective- and Operational-level requirements –System-level requirements –Subsystem-level requirements Design Documents –System Spreadsheet –TPS Reports –Electrical Interface Agreement Document (EIAD) Communication –Subsystem to subsystem –Industry/Academic supporters Budgeting –Mass –Power Control of DINO’s design iterations

DINO PDR 23 October 2015 Colorado Space Grant Consortium System Functional Diagram Imaging Cam A Cam B Legend USB ADCS TR1 TR2 TR3 MAG Sun Sensors x6 Rate Gyro x3 Data Bus Power Lines Thermal +5V Line +/-12V Line MLI Blkts Therm x30 Data Line Comm Tx Ant / Radio / TNC Ext TNC Serial / I 2 C C&DH Flight Computer Interface Board Wireless Power Li-Poly Battery +15V Unreg. Line +28V Line Prim SA Body SA PCB Mechanisms EMC Hinges x4 HOP Tip-Mass Upper LB Tip-Mass TM Cam TM Comm Battery Tether Release Mech TM Lower LB PCB Micro Proc IB Rx Ant / Radio / TNC Tip-Mass Ant / Modem

DINO PDR 23 October 2015 Colorado Space Grant Consortium Daytime Operations Diagram Imaging Cam A Cam B Legend USB ADCS TR1 TR2 TR3 MAG Sun Sensors x6 Rate Gyro x3 Data Bus Power Lines Thermal +5V Line +/-12V Line MLI Blkts Therm x30 Data Line Comm Tx Ant / Radio / TNC Ext TNC Serial / I 2 C C&DH Flight Computer Interface Board Wireless Power Li-Poly Battery +15V Unreg. Line +28V Line Prim SA Body SA PCB Mechanisms EMC Hinges x4 HOP Tip-Mass Upper LB Tip-Mass TM Cam TM Comm Battery Tether Release Mech TM Lower LB PCB Micro Proc IB Rx Ant / Radio / TNC Tip-Mass Ant / Modem

DINO PDR 23 October 2015 Colorado Space Grant Consortium Nighttime Operations Diagram Imaging Cam A Cam B Legend USB ADCS TR1 TR2 TR3 MAG Sun Sensors x6 Rate Gyro x3 Data Bus Power Lines Thermal +5V Line +/-12V Line MLI Blkts Therm x30 Data Line Comm Tx Ant / Radio / TNC Ext TNC Serial / I 2 C C&DH Flight Computer Interface Board Wireless Power Li-Poly Battery +15V Unreg. Line +28V Line Prim SA Body SA PCB Mechanisms EMC Hinges x4 HOP Tip-Mass Upper LB Tip-Mass TM Cam TM Comm Battery Tether Release Mech TM Lower LB PCB Micro Proc IB Rx Ant / Radio / TNC Tip-Mass Ant / Modem

DINO PDR 23 October 2015 Colorado Space Grant Consortium Safe Mode Diagram Imaging Cam A Cam B Legend USB ADCS TR1 TR2 TR3 MAG Sun Sensors x6 Rate Gyro x3 Data Bus Power Lines Thermal +5V Line +/-12V Line MLI Blkts Therm x30 Data Line Comm Tx Ant / Radio / TNC Ext TNC Serial / I 2 C C&DH Flight Computer Interface Board Wireless Power Li-Poly Battery +15V Unreg. Line +28V Line Prim SA Body SA PCB Mechanisms EMC Hinges x4 HOP Tip-Mass Upper LB Tip-Mass TM Cam TM Comm Battery Tether Release Mech TM Lower LB PCB Micro Proc IB Rx Ant / Radio / TNC Tip-Mass Ant / Modem

DINO PDR 23 October 2015 Colorado Space Grant Consortium Mass Budget Total Allocated Mass:18.75 kg Margin: 6.25 kg Total Mass: 25 kg Total Allocated Mass:3.75 kg Margin: 1.25 kg Total Mass: 5 kg

DINO PDR 23 October 2015 Colorado Space Grant Consortium Power Budget Total Allocated Power:22.0 W-hr Margin: 5.5 W-hr Total Power: 27.5 W-hr Total Allocated Power:7.0 W-hr Margin: 1.8 W-hr Total Power: 8.8 W-hr

DINO PDR 23 October 2015 Colorado Space Grant Consortium Power Budget Total Allocated Power:8.0 W-hr Margin: 2.0 W-hr Total Power: 10.0 W-hr Total Allocated Power:6.7 W-hr Margin: 1.7 W-hr Total Power: 8.4 W-hr

DINO PDR 23 October 2015 Colorado Space Grant Consortium Integration and Test Plan

DINO PDR 23 October 2015 Colorado Space Grant Consortium Mission Mode Timeline Launch ICU, DINO Deployment Mission Activation Tether Deployment FITS Deployment Aerofin Deployment Safe Mode Safe Mode Normal Daytime Operations Normal Nighttime Operations Safe Mode Attitude Stabilization

DINO PDR 23 October 2015 Colorado Space Grant Consortium Overall Mission Timeline Launch ICU Deployment DINO Deployment Mission Activation Tether DeploymentFITS Deployment Aerofin DeploymentNormal Science Operations

DINO PDR 23 October 2015 Colorado Space Grant Consortium Launch Phase System CheckLaunch ICU Deploymentfrom Orbiter DINODeployment MissionActivation ICU Separation

DINO PDR 23 October 2015 Colorado Space Grant Consortium Mission Activation Phase Mission Activation Power Up Orbit Sunlit Eclipse Flight System Power up Flight Computer Power UpPower System ActivatedComm, Thermal, ADCS Power Up System Health Check ADCS ActivationCommunication Comm InitializationBeacon TransmissionGround Communication Deployment Phase

DINO PDR 23 October 2015 Colorado Space Grant Consortium Deployment Phase Tether Deployment Orbit Sunlit Eclipse Tether System Health CheckAttitude Stabilization CheckTether DeploymentGround CommunicationTip-Mass Power UpTip-Mass Health CheckTether System Health CheckTether Image Acquisition and Downlink Ground CommunicationTip-Mass Power Down ADCS Stabilization

DINO PDR 23 October 2015 Colorado Space Grant Consortium Deployment Phase FITS Deployment Orbit Sunlit Eclipse Attitude Stabilization Check Solar Array Activation FITS DeploymentGround CommunicationTip-Mass Power UpTip-Mass Health CheckFlight System Health CheckTip-Mass Image DownlinkGround CommunicationTip-Mass Power Down Tip-Mass Image Acquisition

DINO PDR 23 October 2015 Colorado Space Grant Consortium Deployment Phase Aerofin Deployment Orbit Sunlit Eclipse Attitude Stabilization CheckEMC Hinge DeploymentGround CommunicationTip-Mass Power UpTip-Mass Health CheckFlight System Health CheckTip-Mass Image DownlinkGround CommunicationTip-Mass Power Down Tip-Mass Image Acquisition

DINO PDR 23 October 2015 Colorado Space Grant Consortium Science Operations Phase Normal Operations Orbit Sunlit Eclipse Attitude Stabilization Science Image Acquisition Ground CommunicationFlight System Health Check Battery Charging

DINO PDR 23 October 2015 Colorado Space Grant Consortium Safety Current Progress –Safety designs incorporated into PDR design –Good knowledge for what safety aspects must be included Next Step –Safety courses in September Safe parts-manufacturing Safe handling of electrical components Buddy System! –Prototyping Future Plans –Follow DINO’s safety regulations

DINO PDR 23 October 2015 Colorado Space Grant Consortium Subsystem Risk Assessment ADCSC&DHCommImagingMechanismsPowerSoftwareStructuresThermalTip-MassOverallProgramAssessment Performance Schedule Cost Safety Testing Manpower Facilities Overall Subsystem Assessment = low risk = medium risk = high risk = N/A

DINO PDR 23 October 2015 Colorado Space Grant Consortium Contingency Plans RiskLevelResponsible PartyContingency Plan FITS delivery failureHighSystems TeamIncrease efficiency of body- mounted cells; double- deployment of aerofins EMC hinge / aero-fin deliveryMedSystems TeamEliminate aerofins Body-mounted solar panel delivery MedPowerPurchase through / provided by other vendor Power system deliveryMedPowerImplement in-house design of power system Tether deployment failureMedStr/MechUse magnetic torque rods as primary ADCS control FITS deployment failureMedStr/MechGo into low-power mission mode Tether stability, orientation failure HighADCSGo into failed-stability mission mode; cut tether

DINO PDR 23 October 2015 Colorado Space Grant Consortium Issues and Concerns Mass –Structures / Solar Panels do not have enough mass allocated to them –Others are swiftly approaching mass limits Power –Loss of structural size – less room for body-fixed solar panels –Increased mission activation / deployable timeline –Close to budget Complete all trade studies –Comm antenna –Science imaging design –Spacecraft configuration (FITS arrays locations)

DINO PDR 23 October 2015 Colorado Space Grant Consortium Appendix

DINO PDR 23 October 2015 Colorado Space Grant Consortium Mass Budget

DINO PDR 23 October 2015 Colorado Space Grant Consortium Power Budget

DINO PDR 23 October 2015 Colorado Space Grant Consortium Power Budget Cont.

DINO PDR 23 October 2015 Colorado Space Grant Consortium Power Budget Cont.

DINO PDR 23 October 2015 Colorado Space Grant Consortium Tip-Mass Power Budget

DINO PDR 23 October 2015 Colorado Space Grant Consortium Design Deadlines Trade Study75% Confidence Date Deadline Comm Antenna DesignSept 1 st Sept 8 th Imaging Camera DesignAug 18 th Sept 1 st Flight Configuration