payload design criteria for the space test program standard interface vehicle (stp-siv) mr. mike...
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Payload Design Criteria for the Space Test Program
Standard Interface Vehicle(STP-SIV)
Mr. Mike MarlowSTP-SIV Program Manager
Payload Design Criteria for the Space Test Program
Standard Interface Vehicle(STP-SIV)
Mr. Mike MarlowSTP-SIV Program Manager
National Science Foundation Workshop on Small SatelliteMissions for Space Weather and Atmospheric Research
National Science Foundation Workshop on Small SatelliteMissions for Space Weather and Atmospheric Research
National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric ResearchNational Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 22
PurposePurpose
Mission Capabilities Of The STP-SIV Spacecraft Standard Spacecraft To Payload Interfaces
Top-level Detail To Determine If STP-SIV Is A Candidate For Your Mission
Mission Capabilities Of The STP-SIV Spacecraft Standard Spacecraft To Payload Interfaces
Top-level Detail To Determine If STP-SIV Is A Candidate For Your Mission
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STP-SIV Road MapSTP-SIV Road Map2005 2007 2009 2011 2013
SERB Payload AnalysisConcept Definition
Requirements DefinitionIndustry Briefings
Source Selection Documentation
SIV Delivery Order #1 (STPSat-2)Payload, LV Determination
S/C and S/V Development & Test
Source Selection
DO#2 (STPSat-3)
DO#3 (STPSat-4)
1 Apr 06
1 Apr 12
Last Order Date
DO#4 (STPSat-5)
DO# 2 buy long leads at ATPDO# 3 long leads on shelfDO#4 S/C Pre-assembled
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Spacecraft CapabilitySpacecraft Capability
Orbit Altitude 400 – 850 km Orbit Inclination 0° – 98.8° Launch Mass ≤ 180 kg (ESPA driven)SV Stored Volume (cm) 60.9 x 71.1 x 96.5 (ESPA driven)Reliability (at 7 months) 0.90Stabilization Method 3-axisPointing Modes Nadir, Sun Pointing, SafeAttitude Knowledge 0.03° 3σ (goal 0.02° 3σ)Attitude Control 0.1° 3σ (goal 0.03° 3σ)Bus Voltage 28 V ±6Comm Frequency SGLSCommand Rate 2 kbps uplinkTelemetry Rate 2 Mbps downlinkData Storage 8 GbitsPayload Volume 0.14m3
Payload Mass 60 kg
Orbit Altitude 400 – 850 km Orbit Inclination 0° – 98.8° Launch Mass ≤ 180 kg (ESPA driven)SV Stored Volume (cm) 60.9 x 71.1 x 96.5 (ESPA driven)Reliability (at 7 months) 0.90Stabilization Method 3-axisPointing Modes Nadir, Sun Pointing, SafeAttitude Knowledge 0.03° 3σ (goal 0.02° 3σ)Attitude Control 0.1° 3σ (goal 0.03° 3σ)Bus Voltage 28 V ±6Comm Frequency SGLSCommand Rate 2 kbps uplinkTelemetry Rate 2 Mbps downlinkData Storage 8 GbitsPayload Volume 0.14m3
Payload Mass 60 kg+X
+Z
+Y
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Launch Vehicle CompatibilityLaunch Vehicle Compatibility
Minotaur IMinotaur IV
EELV Secondary Payload Adaptor (ESPA)[Atlas and Delta]
Falcon 1 Pegasus/Raptor
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Spacecraft DesignSpacecraft Design
Z
X Y
1 Star Tracker, 1 magnetometer6 sun sensors, 1 GPS receiver, 3 reaction wheels, 3 torque rods
2 fixed/deployed arrays 1 gimbaled arrayGaAs UTJ solar cells30 A-hr Li Ion battery
Payload Interface Panel
Star tracker
Payload Volume
Silver Teflon Coated Radiator
Rigid LV Interface Panel
Sample Payload Configurations
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Topside Sounder Concept on STP-SIVTopside Sounder Concept on STP-SIV
Configuration above shows four deployed 4-m antennas on all four corners of the STP-SIV spacecraft
This effectively yields two, crossed 8-m dipole antennas
Configuration above shows four deployed 4-m antennas on all four corners of the STP-SIV spacecraft
This effectively yields two, crossed 8-m dipole antennas
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Spacecraft to Payload InterfacesSpacecraft to Payload Interfaces
Mechanical
Thermal
Data
Power
EMI
• 100 Watts Orbit Average• 28 V ±6
• Case by Case• System Test on each mission
• 1” grid aluminum panel• #10 fasteners • Stringent environment • Coupled Heat Transfer
• Plate temperatures: -20o to +50o C• 100 Watts Heat Rejection
• Up to 2 Mbps data rate• RS-422 Command and Telemetry• Synchronous data transmission• 8 Bi-Level Discreet I/O channels• 8 analog channels/payload
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Feasibility Study Feasibility Study
Payload to spacecraft compatibility
Payload to payload compatibility
Identifies potential risks
ROM estimate to integrate, test and operate
Payload to spacecraft compatibility
Payload to payload compatibility
Identifies potential risks
ROM estimate to integrate, test and operate
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OpportunitiesOpportunities
Enables space weather communities to leverage S&T spaceflight opportunities Share SIV payload space Rideshare S&T launch opportunities
ESPA on every EELV, payload adaptors on Minotaurs I & IV
Provides cost-effective platform to demo payloads and systems to support space weather programs
Basis for follow-on programs Larger spacecraft class Use of spacecraft to payload “standard” interfaces
Enables space weather communities to leverage S&T spaceflight opportunities Share SIV payload space Rideshare S&T launch opportunities
ESPA on every EELV, payload adaptors on Minotaurs I & IV
Provides cost-effective platform to demo payloads and systems to support space weather programs
Basis for follow-on programs Larger spacecraft class Use of spacecraft to payload “standard” interfaces
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SummarySummary
SIV is a change from past STP business practices Moving away from “one-of-a-kind” spacecraft to gain
benefits of successive spacecraft builds More responsive IDIQ contract, fits with other Space
Development & Test Wing IDIQs
Planned to provide improved access to space for SERB S&T payloads
Potential benefits for broader space community
SIV is a change from past STP business practices Moving away from “one-of-a-kind” spacecraft to gain
benefits of successive spacecraft builds More responsive IDIQ contract, fits with other Space
Development & Test Wing IDIQs
Planned to provide improved access to space for SERB S&T payloads
Potential benefits for broader space community
National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric ResearchNational Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 1212
Payload Design Criteria for the Space Test Program
Standard Interface Vehicle(STP-SIV)
Mr. Mike MarlowSTP-SIV Program Manager
Payload Design Criteria for the Space Test Program
Standard Interface Vehicle(STP-SIV)
Mr. Mike MarlowSTP-SIV Program Manager
National Science Foundation Workshop on Small SatelliteMissions for Space Weather and Atmospheric Research
National Science Foundation Workshop on Small SatelliteMissions for Space Weather and Atmospheric Research
National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric ResearchNational Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 1313
Standard Payload to Spacecraft Interfaces Standard Payload to Spacecraft Interfaces
Mechanical Fasten payload hardware to
spacecraft structure Align payload hardware to
spacecraft reference
Thermal Sense temperature at payload to
spacecraft interface Control temperature at payload
to spacecraft interface by affecting spacecraft side
Mechanical Fasten payload hardware to
spacecraft structure Align payload hardware to
spacecraft reference
Thermal Sense temperature at payload to
spacecraft interface Control temperature at payload
to spacecraft interface by affecting spacecraft side
Payload
1
Payload
2
Spacecraft
M
T
P
D
Power Supply primary main electrical
power to payload Supply redundant main payload
power Supply power for payload heaters
Data Supply bilevel discrete signal from
spacecraft to payload for reset or other switching functions
Provide command data from spacecraft to payload
Provide data transfer from spacecraft to payload (code upload, time synch, attitude, GPS)
Provide digital telemetry data from payload to spacecraft
Provide analog data from payload to spacecraft (state of health monitoring)
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STP Rideshare OpportunitiesSTP Rideshare Opportunities
FY06 FY07 FY08 FY09 FY10 FY11 FY12 FY131Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q
FY09 Minotaur IVPL SelectionDevelopmentMission IntegrLaunch
DMSP F-19SPL SelectionSpecial Studies*Mission UniqueMission IntegrLaunch
STP-2SPL SelectionSpecial Studies*Mission UniqueMission IntegrLaunch
FY11 MinotaurPL SelectionMission IntegrLaunch
DMSP F-20SPL SelectionSpecial Studies*Mission UniqueMission IntegrLaunch
FY13 MinotaurPL SelectionMission IntegrLaunch
Apr 08
Oct 08
Oct 10
Oct 05
Jan 06
Apr 06
There are potentially 30 ESPA-class spacecraft rideshare opportunities
between FY09 – FY13