1. THEMIS SRR Mission Requirements - 1 UCB July 8-9 2003 MISSION REQUIREMENTS Ellen R. Taylor Mission Systems Engineer Space Science Laboratory University of California - Berkeley

2. THEMIS SRR Mission Requirements - 2 UCB July 8-9 2003 Mission Requirements Lifetime and Radiation Fault Tolerance Mission Design Resource Budgets Contamination Requirements Interface Requirements Test Requirements Launch Vehicle Ground Station Mission Requirement Overview

3. THEMIS SRR Mission Requirements - 3 UCB July 8-9 2003 Lifetime M-1. The THEMIS operational system shall be designed for at least a two year lifetime. Rationale: Sufficient to achieve baseline science requirements - allows for two full tail seasons, ensuring conjunction time >188 hrs per year M-2. THEMIS shall meet the NASA orbital debris guidelines of re-entry in NASA Safety Standard (NSS) 1740.14 Rationale: Required per NASA guidelines: Re-entry in <25 yrs and debris footprints <8 m2

4. THEMIS SRR Mission Requirements - 4 UCB July 8-9 2003 Radiation M-3. THEMIS shall be designed for a total dose environment of 33 krad/year (66 krad total) (TBR) Rationale: Survival in predicted radiation environment - based on dose/depth curve calculations indicating 33 krad TID behind 5mm Al for a one year mission (includes a RDM of 2 for uncertainty of model and variability of environment). From PAIP: Parts shall meet these criteria based on manufactures data sheet, demonstrated technology hardness, or lot testing. Shielding or special packaging may be used to achieve the desired tolerance. M-4. THEMIS shall be Single Event Effect (SEE) tolerant and immune to destructive latch-up. Rationale: Ensures operability in radiation environment. Protection occurs on several levels: Parts, Local Circuit Protection, Scrubbing, Reset. From PAIP: Parts shall be SEL-immune to a LET >80 MeV-cm2/mg – TBR), or else shall be protected against damage by a protection circuit. Parts that may affect critical functions that could damage the instrument shall be SEU immune, or else shall use a Triple-Modular-Redundancy scheme to avoid an single SEU causing a failure. Parts shall meet these criteria based on manufactures data sheet, demonstrated technology hardness, or lot testing

5. THEMIS SRR Mission Requirements - 5 UCB July 8-9 2003 Fault Tolerance and Redundancy M-5. To the maximum extent possible, THEMIS operational system shall be designed to be single fault tolerant and still meet minimum mission success criteria Rationale: Project guidelines direct the design of the most robust and fault tolerant system within the constraints of allocated resources. Reflects accepted design practice commensurate with mission scope; use of redundancy; and system design promoting graceful degradation in the event of an anomaly or failure. M-6. THEMIS Probe 3 or 4 shall be capable of replacing any other probe during the minimum mission Rationale: Allows for failure of one probe and still meet minimum mission success

6. THEMIS SRR Mission Requirements - 6 UCB July 8-9 2003 Failure Recovery M-7. Each Probe shall have a viable safe-hold mode after carrier separation Rationale: Allows for anomaly investigation and correction from the ground. Safe-hold mode is defined as power safe, thermally safe, able to communicate with ground throughout orbit, etc. Safe-hold mode will be fully defined early in the design process. M-8. THEMIS Probes shall implement Failure Detection and Correction (FDC). Rationale: Indicates some autonomy in detecting and correcting faults.

7. THEMIS SRR Mission Requirements - 7 UCB July 8-9 2003 Mission Design M-9. THEMIS shall perform science observations with identical probes in multiple period, near-equatorial orbits (five probes required for baseline science, four probes required for minimum) Rationale: Supports science requirements - multiple spacecraft allows probes to simultaneously measure substorm signatures over long distances along the magnetotail. M-10. Each THEMIS Probe shall have a unique ID that can not be changed on-orbit. Rationale: All probes share the same frequency. Required to contact one probe at a time. M-11. The THEMIS probe conjunctions shall be coordinated with ground- based observations during prime geo-tail season Rationale: Fundamental part of science mission – space-based observations coordinated with ground-based observations to aid in determining the onset of substorms (M-12 through M-18: Orbit Design will be discussed later)

8. THEMIS SRR Mission Requirements - 8 UCB July 8-9 2003 Resource Budgets - Mass M-19. THEMIS maneuvers shall be optimized to not exceed a delta-V of 566m/s +15% contingency (TBR) (for limiting case P1) Rationale: Design decision based on current best estimate of Delta-V plus some contingency for design margin. Fixing number allows sizing of propellant tanks. M-20. All THEMIS Probes shall have (TBR) propellant margin at launch Rationale: Allows for operational errors, possible anomalies after launch. M-21. No THEMIS Probe shall exceed a dry mass of 70.8kg Rationale: 62.0 kg CBE + 14.4% contingency M-22. Each THEMIS Probe shall be designed to accommodate a 82kg (TBR) dry mass, Delta-V of 650m/s (TBR), and a (TBR) propellant margin at launch Rationale: System design allocation accommodates dry mass 62.0kg CBE + 14.4% contingency (not-to-exceed 70.8kg) plus 16% Program Margin; and a delta-V 566m/s + 15% contingency (not-to-exceed 650m/s) plus propellant margin at launch. Sizes propellant tanks. Note: Numbers are TBR due to on-going tank trade study and procurement.

9. THEMIS SRR Mission Requirements - 9 UCB July 8-9 2003 Mass Allocation Flow-down from M-21: No THEMIS Probe shall exceed a dry mass of 70.8kg IN-5. The Instrument Payload shall not exceed a mass of 23.6 kg. IN-6. No component of the Instrument Payload shall exceed the allocated mass budget PB-9. The Probe Bus shall not exceed a dry mass of 47.2 kg (instrument payload not included) PB-10. No Probe Bus subsystem shall exceed the allocated mass budget INSTRUMENTCBE (kg) Contingency Allocated (kg) FGM 1.35*0.111.46 SCM 1.50*0.181.68 ESA 2.080.172.24 SST 1.260.161.42 EFI 11.22*1.1812.40 IDPU 3.540.894.43 Total21.0 2.7 23.6 SUBSYSTEMCBE (kg) Contingency Allocated (kg) ACS 0.37 0.04 0.41 Avionics 2.050.412.46 RF/Comm 2.60 0.27 2.87 Power 5.96 0.89 6.85 Harness 1.25 0.31 1.56 Propulsion 6.88 0.69 7.57 Thermal 0.90 0.14 1.04 Mechanical 20.99 3.42 24.41 Total 41.0 6.2 47.2 Rationale: 21.0 kg CBE + 12.4% contingency Rationale: 41.0 kg CBE + 15.1% contingency Note: Tables are summary only. System allocations in MRD. Subsystem allocations are controlled separately in detailed budget. * Includes boom and harness, sensor only allocation provided in detailed budget.

10. THEMIS SRR Mission Requirements - 10 UCB July 8-9 2003 Resource Budgets - Power M-23. No THEMIS Probe shall exceed an on-orbit power draw of 29.24 W Rationale: 24.5 W CBE + 19.3% contingency M-24. The Probe power system shall be designed to accommodate an EOL on-orbit average power of 41.5W. Rationale: System design allocation is 24.5 W CBE + 19.3% contingency (not-to-exceed 29.24W) plus 42% Program Margin. Sizes solar array area and battery capacity. M-25. Each Probe shall be designed to achieve electrical energy balance over an orbit assuming a 30 minute transmitter power on time and 180 minute eclipse. Rationale: Electrical power system must be sized to accommodate peak and on-orbit power loads (eclipse, downlink, etc). Transmitter on-time and eclipse duration indicates system design trade considering power and thermal constraints versus downlink budget and orbit optimization.

11. THEMIS SRR Mission Requirements - 11 UCB July 8-9 2003 Power Allocation Flow-down from M-23: No THEMIS Probe shall exceed an on-orbit power draw of 29.24 W IN-7. The Instrument Payload shall require less than 14.7 W (on-orbit average) IN-8. No component of the Instrument Payload shall exceed the allocated power budget PB-11. The Probe Bus shall require less than 14.5 W average power PB-12. No Probe Bus subsystem shall exceed the allocated power budget INSTRUMENTCBE (kg) Contingency Allocated (kg) FGM 0.01*0.000.01 SCM 0.08*0.010.09 ESA 1.87*0.142.01 SST 0.85*0.211.06 EFI 0.48*0.050.53 IDPU 8.852.2111.06 Total12.1 2.6 14.8 SUBSYSTEMCBE (kg) Contingency Allocated (kg) ACS 0.13 0.01 0.14 Avionics 5.00 1.00 6.00 RF/Comm 5.250.796.04 Thermal 2.00 0.30 2.30 Total 12.4 2.1 14.5 Rationale: 12.1 W CBE + 22.3% contingency Rationale: 12.4 W CBE + 17.0% contingency * Includes sensor only. Power allocation for instrument support electronics in IDPU provided in detailed budget. Note: Tables are summary only. System allocations in MRD. Subsystem allocations are controlled separately in detailed budget.

12. THEMIS SRR Mission Requirements - 12 UCB July 8-9 2003 Resource Budgets - Data M-26. Each THEMIS Probe shall be designed to accommodate 750 Mbits/orbit (uncompressed) Instrument science and housekeeping data and 87 Mbits/orbit Probe Bus housekeeping data. Rationale: Reflects expected instrument data rate collected over an orbit for all mission modes (survey and burst); and expected probe data rate (1kpbs) collected for P3,4,5 (1 day orbit). Drives need to reduce data rate for P1 (4 day orbit) and P2 (2 day orbit). M-27. THEMIS shall be capable of storing 1 orbit + 1 days worth of Instrument and Probe Bus housekeeping data. Rationale: Provides contingency if ground station pass is missed.

13. THEMIS SRR Mission Requirements - 13 UCB July 8-9 2003 Program Margin M-29. All resource budgets (mass, power, data) shall show sufficient positive margin at each project milestone Rationale: Sufficient margins are evaluated at each major review and addressed in Risk Mitigation Plan. Mass and Power resources are considered ‘high’ risk (triggering risk mitigation plan) if they don’t meet the margin schedule.

14. THEMIS SRR Mission Requirements - 14 UCB July 8-9 2003 Contamination - Magnetics M-30. AC magnetic noise radiated by the Probe and the other instruments shall not exceed 10pT/Hz^1/2 @ 10Hz and 1pT/Hz^1/2 at 1kHz at the SCM sensor Rationale: Sensitivity required by SCM M-31. DC magnetic noise radiated by the Probe and the other instruments shall not exceed 1nT at the FGM sensor Rationale: Sensitivity required by FGM M-32. All THEMIS elements shall comply with the Magnetics Cleanliness standard described in the THEMIS Magnetics Cleanliness Plan. Rationale: Adherence to document ensures residual and induced magnetic fields does not corrupt mission science

15. THEMIS SRR Mission Requirements - 15 UCB July 8-9 2003 Contamination - Electrostatic M-33. Quasi-DC voltages produced by the Probe and the other instruments shall not affect the quality of the EFI measurement Rationale: Sensitivity of EFI M-34. All THEMIS elements shall comply with the THEMIS Electrostatic Cleanliness (ESC) Plan Rationale: Adherence to document mitigates potential of contaminating quasi-DC voltages affecting quality of EFI measurement. Compliance will be assured via a ESC Czar.

16. THEMIS SRR Mission Requirements - 16 UCB July 8-9 2003 Contamination - Molecular M-35. The molecular contamination of the ESA sensor shall be less than 0.01 ug/cm^2 (TBR). Particulate level TBD. Rationale: ESA Contamination (instrument driver) M-36. The molecular contamination of the SST sensor shall be less than 0.1 ug/cm^2 (TBR). Particulate level TBD. Rationale: SST Contamination M-37. All THEMIS Elements shall comply with the THEMIS Contamination Control Plan Rationale: Adherence to document ensures contamination of sensitive portions of the Probes by condensable and particulates does not prevent the ESA and SST from meeting its performance requirements

17. THEMIS SRR Mission Requirements - 17 UCB July 8-9 2003 Interfaces M-38. All hardware shall meet the general electrical system requirements documented in the THEMIS Electrical System Specification. Rationale: Adherence to document provides electrical design guidelines and alleviates interface problems during system integration M-39. All THEMIS Elements shall be compatible per their ICDs Rationale: Adherence to ICDs ensures interface requirements are met

18. THEMIS SRR Mission Requirements - 18 UCB July 8-9 2003 Test Requirements M-40. All THEMIS components shall verify mission performance requirements are met per the Verification Plan and Environmental Test Specification Rationale: Supports mission science – verifies performance is as expected prior to launch M-41. All THEMIS components shall survive and function prior to, during and after exposure to the launch and space environments described in the Verification Plan and Environmental Test Specification Rationale: Adherence to document ensures all elements are subjected to expected launch and space environments as part of a comprehensive test program M-42. All THEMIS components shall be sufficiently testable during all levels of integration and test Rationale: Ensures system function and performance throughout integration and test phase. Drives subsystem designs to include integrated test capability

19. THEMIS SRR Mission Requirements - 19 UCB July 8-9 2003 Launch Vehicle M-43. THEMIS shall be compatible with a Delta II 2925-10 Rationale: Provides sufficient performance capability and reliability to place THEMIS Probes into the desired initial parking orbit M-44. Within the schedule cap (March 2007), the THEMIS launch date shall not be restricted Rationale: System is sized to allow launch any day of the year. A launch date of August 2006 plus or minus 2 months is preferred in accordance with schedule and minimum time to prime observation season. Launch period would allow time to commission the probes prior to the operational period starting in December 2006. The launch window is approximately 40 minutes every day. M-45. The THEMIS Probe Carrier Assembly (5 Fueled Probes plus Probe Carrier) mass-to-orbit shall not exceed 807kg. Rationale: Preliminary estimate of Delta 2925-10 lift capability

20. THEMIS SRR Mission Requirements - 20 UCB July 8-9 2003 Launch Vehicle Derived M-46. The fundamental frequency of the Probe Carrier Assembly (Probe Carrier + 5 Fueled Probes) in launch configuration shall be greater than 15 Hz in lateral and 35 Hz in axial. M-47. The CG location of the Probe Carrier Assembly (Probe Carrier + 5 Fueled Probes) shall be within TBD of the PCA centerline. Rationale: Delta II requirements.

21. THEMIS SRR Mission Requirements - 21 UCB July 8-9 2003 Ground Stations M-48. THEMIS shall be compatible with BGS, USN, TDRSS, and NASA/GN Rationale: Ensures data downlink requirements during operations phase are met with dedicated ground station (BGS), secondary (USN) and back-up (NASA/GN). TDRSS provides continuous coverage as needed during launch, early operations phase, maneuvers and potential anomalous conditions. M-49. THEMIS shall be S-Band, CCSDS-compatible and COP-1 compatible Rationale: Provides a standard to simplify back-up by other stations

22. THEMIS SRR Mission Requirements - 22 UCB July 8-9 2003 Downlink Rates M-50. THEMIS Probes shall be capable of downlinking all stored data for each Probe: 325 Mbits/orbit science and instrument housekeeping data (assumes x2 compression) plus 87 Mbits/orbit Probe Bus housekeeping data. Rationale: Reflects expected data volume. M-51. THEMIS Probes shall be capable of downlinking minimum housekeeping data from all probes at least once a day. Rationale: Operational Goal. Safe-guards against anomaly going unnoticed. M-52. THEMIS Probes shall be capable of downlinking all data within 30 minutes per day per probe (maximum transmitter on time). Rationale: Reflects power generation capabilities of body mounted solar arrays. Affects thermal and data rates. M-53. THEMIS Probes shall provide housekeeping telemetry downlink capability from maximum altitude (apogee of 30RE) Rationale: Desire to know state of probe at any time (no black-out)

23. THEMIS SRR Mission Requirements - 23 UCB July 8-9 2003 Uplink Rates M-54. THEMIS Probes shall be capable of receiving ground commands to maximum altitude (apogee of 30RE) Rationale: Desire to communicate with probe at anytime (no black-out) M-55. The THEMIS uplink data rate shall be 1 kbps for all probes Rationale: Baseline uplink rate

24. THEMIS SRR Mission Requirements - 24 UCB July 8-9 2003 Link Budget M-56. The S-Band uplink and downlink shall have a link margin of ≥ 3dB at all points in the orbit through all mission phases Rationale: Ensures a stable and reliable RF communications path. Design driven by limiting cases (P-1). Drives need for variable downlink rates M-57. The THEMIS link analysis shall assume a 10E-6 BER downlink and 10E-7 BER uplink Rationale: Downlink BER minimizes error rate of data recovered after transmission and recovery at ground station. Uplink BER (along with command checking) precludes the execution of an invalid command

25. THEMIS SRR Mission Requirements - 25 UCB July 8-9 2003 Ranging, Gnd Processing M-58. Probe orbits shall be known to an accuracy of 10km at Perigee and 100km at Apogee. Rationale: Adequate for ground station antenna pointing. Meets Science Requirements. M-59. The THEMIS Ground System shall monitor and take appropriate action to maintain the health and safety of the Probes Rationale: Defines Ground System Role. M-60. The THEMIS Ground System shall calculate and propagate all orbit and attitude parameters necessary for orbit maintenance and attitude control of each Probe. Rationale: Design decision to simplify Probe Bus design, given spinning probes are highly stable once fully deployed and spinning.