1. Payload Design Criteria for the Space Test Program Standard Interface Vehicle (STP-SIV) Mr. Mike Marlow STP-SIV Program Manager Payload Design Criteria for the Space Test Program Standard Interface Vehicle (STP-SIV) Mr. Mike Marlow STP-SIV Program Manager National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research

2. National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 2 Purpose  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

3. National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 3 STP-SIV Road Map 2005 2007 2009 2011 2013 SERB Payload Analysis Concept Definition Requirements Definition Industry 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 ATP DO# 3 long leads on shelf DO#4 S/C Pre-assembled

4. National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 4 Spacecraft Capability Orbit Altitude400 – 850 km Orbit Inclination0° – 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)0.90 Stabilization Method3-axis Pointing ModesNadir, Sun Pointing, Safe Attitude Knowledge0.03° 3σ (goal 0.02° 3σ) Attitude Control0.1° 3σ (goal 0.03° 3σ) Bus Voltage28 V ±6 Comm FrequencySGLS Command Rate2 kbps uplink Telemetry Rate2 Mbps downlink Data Storage8 Gbits Payload Volume0.14m 3 Payload Mass60 kg Orbit Altitude400 – 850 km Orbit Inclination0° – 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)0.90 Stabilization Method3-axis Pointing ModesNadir, Sun Pointing, Safe Attitude Knowledge0.03° 3σ (goal 0.02° 3σ) Attitude Control0.1° 3σ (goal 0.03° 3σ) Bus Voltage28 V ±6 Comm FrequencySGLS Command Rate2 kbps uplink Telemetry Rate2 Mbps downlink Data Storage8 Gbits Payload Volume0.14m 3 Payload Mass60 kg +X +Z +Y

5. National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 5 Launch Vehicle Compatibility Minotaur I Minotaur IV EELV Secondary Payload Adaptor (ESPA) [Atlas and Delta] Falcon 1 Pegasus/Raptor

6. National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 6 Spacecraft Design Z X Y 1 Star Tracker, 1 magnetometer 6 sun sensors, 1 GPS receiver, 3 reaction wheels, 3 torque rods 2 fixed/deployed arrays 1 gimbaled array GaAs UTJ solar cells 30 A-hr Li Ion battery Payload Interface Panel Star tracker Payload Volume Silver Teflon Coated Radiator Rigid LV Interface Panel Sample Payload Configurations

7. National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 7 Topside 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

8. National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 8 Spacecraft 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: -20 o to +50 o 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

9. National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 9 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

10. National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 10 Opportunities  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

11. National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 11 Summary  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

12. National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 12 Payload Design Criteria for the Space Test Program Standard Interface Vehicle (STP-SIV) Mr. Mike Marlow STP-SIV Program Manager Payload Design Criteria for the Space Test Program Standard Interface Vehicle (STP-SIV) Mr. Mike Marlow STP-SIV Program Manager National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research

13. National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 13 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)

14. National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 14 STP Rideshare Opportunities FY06FY07FY08FY09FY10FY11FY12FY13 1Q2Q3Q4Q1Q2Q3Q4Q1Q2Q3Q4Q1Q2Q3Q4Q1Q2Q3Q4Q1Q2Q3Q4Q1Q2Q3Q4Q1Q2Q3Q4Q FY09 Minotaur IV PL Selection Development Mission Integr Launch DMSP F-19 SPL Selection Special Studies* Mission Unique Mission Integr Launch STP-2 SPL Selection Special Studies* Mission Unique Mission Integr Launch FY11 Minotaur PL Selection Mission Integr Launch DMSP F-20 SPL Selection Special Studies* Mission Unique Mission Integr Launch FY13 Minotaur PL Selection Mission Integr Launch Apr 08 Oct 08 Oct 10 Oct 05 Jan 06 Apr 06 There are potentially 30 ESPA-class spacecraft rideshare opportunities between FY09 – FY13