Universe of SERB-Approved Payloads

1. MidSTAR IIUnited States Naval AcademySmall Satellite ProgramProf. Billy R. Smith, Jr., PhDDirector

2. Universe of SERB-Approved Payloads • Mission requirements have been chosen with the intent of accommodating as many SERB-approved payloads as possible. The 2005 SERB List was subjected to a frequency analysis to determine a range of values that MIDSTAR could support: • 300,000 cm3 of volume accommodates 80% of experiments; • 80 kg, the mass limit for mod 2, accommodates 70% of experiments; • 100W average power accommodates 70% of experiments; and • 100 kbps data rate satisfies 90% of experiments. • The baseline configuration of MidSTAR-class satellites will assume maximum capacity in all onboard systems. Trade-offs will be made in the design of specific spacecraft as necessary to meet the needs of the payloads manifested.

3. Securing a Launch • Acquire manifest on DOD Space Test Program (STP) funded launch vehicle • Must carry payload(s) or experiment(s) on current SERB list • STP is authorized to procure s/c to support experiments • Other experiments welcomed on no-cost/no-interference/resources-available basis • Three possible launch windows • MidSTAR-2 Lite: Defense Meteorological Satellite Program (DMSP) -19 FY09 • MidSTAR-2 Professional Edition: STP-2 FY10 or DMSP-20 FY11 • DMSP orbits: 830-km, sun-synchronous (99 deg inclination)

4. MidSTAR-1 Manifest • Launch vehicle: STP-1 Atlas V, projected launch date 2 Nov 2006 • SERB Payloads • Internet Communications Satellite (ICSat) (USNA Aero Dept) • Configurable Fault Tolerant Processor (CFTP) (Naval Postgraduate School) • Other Payloads • MicroDosimeter NanoSensor Experiment (MiDN) (USNA Aero Dept and US Space Biological Research Institute) • MicroElectroMechanical Sensor Experiment (MEMS) (USNA EE Dept and Johns Hopkins Applied Physics Laboratory) • NanoChem Sensor Unit (NCSU) (NASA Ames Research Center) • Eclipse (Eclipse Energy Systems, Inc. and NASA Goddard Space Flight Center)

5. 38in 28 in

6. Assembly

7. MidSTAR I Characteristics • Obeys the physical, electrical and environmental constraints of the ESPA ring; • Linux PC-based Command & Data Handling (C&DH) System with open source software • Uplink and downlink frequencies in military spectrum (Uplink: 1.767 GHz, downlink 2.20226 GHz) • 68.4 kbps or better GMSK • 39 V Power at 25 W average

8. MidSTAR II Mission Statement • Support primary STP mission for two years; support additional USNA and NASA experiments for two years; demonstrate additional space operation capability such as attitude control, redundant power systems, or light sensing.

9. Design Improvement • Possible Mission improvements are: • Reduce the overall mass • Dual redundant power system • Improved Thermal control • S/C to S/C link with MidSTAR-1 • Attitude Control • Onboard Ethernet-based Local Area Network (LAN)

10. MidSTAR II Success criteria • 100% success requires: • Support of primary and secondary science payloads for two years • Repeated, successful demonstration in space of one advanced operation capability such as: Attitude control Thermal control Low resolution camera S/C to S/C link with MidSTAR-2

11. MidSTAR II Success criteria • 50% Success criteria: • Support of primary and secondary science payloads for two years • Single successful demonstration of advanced operation capability • 25% Success criteria: • Support of primary payload for sufficient length of time to gather significant reducible data for payload owner

12. Mission Timeline