1. ISS RapidScat Ops TIM1 11 December 2012 ISS RapidScat Payload Ops TIM Payload Overview JPL RapidScat Team 11 December 2012

2. ISS RapidScat Ops TIM2 11 December 2012 Outline Scatterometer Science Overview RapidScat Programmatic Overview RapidScat Instrument Description Ground System Data Flow and Functions Operations Concept Highlights Comments

3. ISS RapidScat Ops TIM3 11 December 2012 Scatterometer Science Overview

4. ISS RapidScat Ops TIM4 11 December 2012 NASA’s Radar Scatterometry NASA pioneered and established modern radar scatterometry for the measurement of sea surface wind speed and direction measurements (ocean vector winds) For more than a decade, QuikSCAT provided dynamic views of air-sea parameters that enabled improved understanding of the process and generated many applications Global Winds as Viewed by QuikSCAT QuikSCAT Sees Hurricane Katrina SASS-A on SeaSAT (1978) – Concept Demo NSCAT on ADEOS (1996-1997*) SeaWinds on QuikSCAT (1999-Present) [Stopped Rotating] SeaWinds on ADEOS-II (2002- 2003*) * Terminated due to solar panel failure Scanning Pencil Beam Scatterometers Fixed Fan Beams Scatterometers

5. ISS RapidScat Ops TIM5 11 December 2012 Radar scatterometery measures sea surface signatures, by transmitting pulses at optimized frequencies toward optimized incidence angles while receiving the “back-scattered” echoes, in order to derive vector winds (speed and direction) 1800km Scanning pencil beams [SeaWinds/QuikSCAT] High Winds & Rough Sea (Stronger Return Signals) Radar Transmit Pulses Undetected Specular (unreturned) Signals Detected Return Signals Radar Transmit Pulses Undetected Specular (unreturned) Signals Detected Return Signals Radar scatterometer is designed to observe sea surface from multiple viewing angles, to retrieve vector winds, and to have wide swath coverage, and is flown in sun synchronous repeat orbits Well-established geophysical model function at Ku-band to retrieve winds (top): wind speed/incidence angle/radar cross-section (bottom); wind direction/incidence angle/radar cross-section Fixed fan beams [ASCAT] Low Winds & Calm Sea (Weaker Return Signals) 1100km Single Rotating Pencil- Beam Antenna Fixed Fan-Beam Antennas Fan-Beam Antenna Footprint Scanning Antenna Footprints Resolution Cell Formed by Range or Doppler Filtering Radar Scatterometry: How It Works

6. ISS RapidScat Ops TIM6 11 December 2012 Science and Application from Ocean Winds Risien & Chelton (2008) Multi-Year Mean January Winds from QuikSCAT QuikSCAT Winds & Hurricane Frances 2004 Ocean Winds: – Drive upper ocean circulation and ocean waves/coastal swell – Determine exchange of water vapor, heat and carbon dioxide between ocean & atmosphere – Are central elements in severe weather events and related damage – Are key factors for nutrient availability for ocean phytoplankton Need for Observations: – Understanding ocean wind processes – Weather & marine forecast support – Development and evaluation of weather and climate models – More frequent and better resolution observations to improve current models and understanding of the processes are important

7. ISS RapidScat Ops TIM7 11 December 2012 ISS-RapidScat Provides Valuable Science Observations Science/Observation Objectives Continue more than 10-year Ku-band based vector winds observations Investigate the global diurnal cycle and remove the diurnal effect on scatterometer-based ocean vector winds [diurnal data currently unavailable] Improve cross-calibration of and provide additional measurements to the international OVW constellation Coverage 48 hrs nearly full coverage within ±57° latitudes (vs. QuikSCAT 24 hrs 90% global) Combined RapidScat with ASCAT may achieve coverage similar to QuikSCAT RapidScat 24-36-48 hrs Unblocked Coverage

8. ISS RapidScat Ops TIM8 11 December 2012 ISS Offers Platform for Evaluating Diurnal Variability and Climatology Question: Different sun synchronous scatterometers yield very different yearly average wind signatures. Why? Strong diurnal cycles of the near-surface winds, stress, curl and divergence have been identified but not well understood due to lack of data Significant differences in the QuikSCAT and ASCAT climate models can be accounted for solely based on un-sampled diurnal variability ISS Contribution: In addition to calibration differences between scatterometers, differences in diurnal sampling can lead to different climate models Resolving systematic subdiurnal variability requires multiple scatterometers in synchronized sun-synchronous orbits or a single scatterometer on a non-sun- synchronous platform such as ISS ISS provides an excellent platform for diurnal observations

9. ISS RapidScat Ops TIM9 11 December 2012 RapidScat Programmatic Overview

10. ISS RapidScat Ops TIM10 11 December 2012 Concept Highlights Concept: Approved at SSPCB by ISS Program Manager for Launch on SpaceX 4 Payload: Existing SeaWinds engineering model (EM) and flight spare assemblies – Modify for accommodation on ISS  Implement power converter (120Vdc from Columbus to 48Vdc for Instrument)  Design and fabricate 0.75 m diameter parabolic reflector (2 pencil beams) and mount to existing EM spin mechanism  Implement science data interface (continuous 40 kbps) with buffering capability  Adjust timing for operation at 380 to 430 km altitude – Package for robotic installation onto Columbus SDX site using a nadir-viewing adapter – Operate the instrument for 2 years

11. ISS RapidScat Ops TIM11 11 December 2012 Concept Highlights Operations: Operated by POIC using procedures developed and approved by JPL – Radar parameters may be adjusted daily via routine table uploads provided by JPL JPL leads instrument check-out and calibration operations JPL is responsible for science data processing and archiving Data Analysis and Application: Reuse QuikSCAT/SeaWinds science data processing system – Modify for ingesting ISS ancillary data (ephemeris, attitude, time correlation) and science telemetry files from the payload Existing Ocean Vector Winds science team (Potential) NOAA for operational forecasting – Goal only, no operational or data latency requirements Implementation Plan: NASA NPR 7120.8, commercial parts, streamlined review and mission assurance; full support for safety reviews – NPR 7120.8 describes project management requirements for “technology demonstration missions” GFE: 2 CEPAs, 1 passive FRAM, STEP test set Environmental testing as required to satisfy launch and safety requirements

12. ISS RapidScat Ops TIM12 11 December 2012 ISS-RapidScat Team

13. ISS RapidScat Ops TIM13 11 December 2012 ISS-RapidScat Schedule Highlights 8/7/12: SSPCB approved the project to proceed with formulation work; NASA Research Office is the programmatic oversight and funding organization – PD organization formed and RIO personnel assigned; – First programmatic TIM at JPL on 8/23/12; integration working group kick-off at JSC on 9/7/12; PIM weekly tag-ups after that 10/03/12: RICB reviewed site selection evaluation, with the team provided analyses that are affected by different sites and trades – Assigned CEF-SDX and targeted for SpaceX launch in Feb 2014, a much accelerated schedule than proposed; formally listed in 11/13/12 FPIP- ISS Flight Plan – PD to determine feasibility of cost and schedule by Jan 2014 PDR 11/7/12: Held Safety Phase 0 TIM with Safety Panel – Found no significant issues with hazard control design 11/27-28: Held interface TIM with ESA/Astrium, baselining COL-EPF ICD and VCP 12/11-12: POIF TIM

14. ISS RapidScat Ops TIM14 11 December 2012 Schedule Original schedule was for July ‘14 launch SSPCB asked for acceleration to Feb ’14 launch on SpaceX-4 Schedule to be “baselined” following PDR

15. ISS RapidScat Ops TIM15 11 December 2012 RapidScat Instrument Description

16. ISS RapidScat Ops TIM16 11 December 2012 ISS-RapidScat Configuration at SDX Site Nadir Pointing Adapter on CEPA (SAGE example) Support/Transition Structure Passive FRAM CEPA SDN FRAM-based Envelope (Expected to be HDEV) Reflector Command & Data Subsystem CEPA Electronics Subsystem Instrument Dual-Feed Strut s Spin Mechanism Assembly FRAM-Based Envelope 800-1000km Scanning Antenna Ground Footprints Single Rotating Antenna with Dual Beams SDN PD Full Envelope Nadir Pointing Adaptor Instrument 45° 5° HDEV Envelope Nadir Antenna Rotates @ 18 rpm; Off- Pointing Beams Sweep An Annulus on the Ground

17. ISS RapidScat Ops TIM17 11 December 2012 Modifications to Inherited Hardware Radar timing will be modified to accommodate lower altitude Replace V-band clamp pyro w/ NEA Refurbish rotary joints (still under evaluation) Modify CDS Chassis to fit new configuration Modify thermal management Flight Software No change to inherited CDS FSW New FSW is confined to DIB ANTENNA SUBSYSTEM (SAS) ELECTRONICS SUBSYSTEM (SES) COMMAND & DATA SUBSYSTEM (CDS) New Instrument Hardware for ISS Implementation P/L structure and thermal subsystem (radiators and MLI) for packaging on GFE’d P/L Adaptor (CEPA) Nadir-looking adapter Antenna assembly (reflector and feeds) Power converter (120 Vdc ISS power to 40 Vdc P/L power) Digital Interface Bridge to mediate ISS and SeaWinds CD&H interfaces System wiring harness Power and signal cables from P/L to Adaptor RapidScat Instrument Implementation EGSE Rack and EM SES, with EM SAS in background SeaWinds CDS S/N 003 under test, beside QuikSCAT CDS S/N EM001

18. ISS RapidScat Ops TIM18 11 December 2012 RapidScat Flight System Functional Block Diagram Survival Heaters Existing SES Power Converter Traveling Wave Tube Amplifier SES Command and Signal Processor Exciter and Synthesizer Receiver Transmit/Receive Switch Assembly Transmit Power Monitor T/R Switch Drivers Waveguide, Beam A Waveguide Beam B Routing Switch Network Existing Scatterometer Electronics Subsystem (SES) Grid Control I, Q Video Doppler Attenuator Control Cmds & Data Dual Pencil Beam Reflector and Feeds Power Converter Unit Digital Interface Bridge 48Vdc 120Vdc 48Vdc SpaceX Dragon Ethernet Columbus EPF Discrete Controls Existing Scat Antenna Subsystem (SAS) Spin Mechanism and RF Rotary Joint Existing Command and Data Subsystem (CDS) Cmds & Data Power Switching & Distribution Survival Heaters Survival Heater Power 1553 Survival Heater Power Instrument Data Processor New Elements EM Flight Spare

19. ISS RapidScat Ops TIM19 11 December 2012 Major System Elements Digital Interface Bridge (DIB) Receives commands and transmits health and status over US 1553 Transmits mission telemetry (science data) over US Ethernet Power Conditioning Unit (PCU) Converts ISS 120V power to 48V Controls instrument on/off/survival heat via XCMU Command & Data Subsystem (CDS) [with DIB and PCU added] Receives and processes instrument commands forwarded by DIB from US 1553 Collects digitized measurement and health/status data, packages the data, and delivers to DIB to be forwarded to US Ethernet Issues command to the SES and SAS Controls power to the TWTA Scatterometer Electronics Subsystem (SES) [with timing modification] Provides RF signal routing for different instrument modes [commandable], including science observation mode and internal calibration mode Receives the RF signals captured by the antenna or routed by the calibration loop, conditions the signals and coverts them to digital form, performs signal processing Traveling Wave Tube Amplifier (TWTA) [Housed within the same enclosure as the SES, but powered separately] Generates 13.4GHz radio-frequency (RF) 100-Watt pulses at about 190 pulses per second [commandable] for transmission by the antenna subsystem Scatterometer Antenna Subsystem (SAS) [with new reflector antenna] Radiates the RF pulses toward the ocean, through the antenna spun by the spinning mechanism assembly at 18 revolution per minute, and captures the reflected RF signals from the ocean surfaces Nadir Pointing Adapter (NPA) [new] Provides transitional structure for pointing the instrument spin axis in nadir direction Provides harness for electrical connection between the Instrument and the ISS (EPF)

20. ISS RapidScat Ops TIM20 11 December 2012 ISS SCAT Parameters Frequency13.4 GHz Bandwidth250 kHz Pulse Width1 ms PRI5-6 ms Tx Peak Power100 W Ant Size0.75 x 0.75 m Ant PolarizationH and V Rotary Joint 2 channel Ku-band Spin Rate18 rpm NEσ 0 – 30 dB Backscatter Resolution 16 x 2 km Swath Width 800-1000 km Mass (with CEPAs)552 kg Power400 W Data Rate40 kbps continuous ISS Accommodation Altitude380 – 430 km Orbit Inclination51.6 deg LocationColumbus SDX Site Pointing Control+/- 2 deg (3sigma) Pointing Knowledge+/- 1 deg (3sigma) Pointing StabilityCapability of ISS Command I/F1553 Data InterfaceEthernet (10 Base T) RapidScat Characteristics and Accommodation

21. ISS RapidScat Ops TIM21 11 December 2012 Instrument Modes The instrument can be configured into the following modes: – Power-Off Mode. The instrument is completely turned "off” – Survival Heat. All electronics are off, 120V survival heaters are on – Thermal Safe Mode: In this mode, the PCU and DIB are powered on, other electronics are off and replacement heaters are on, powered from PCU 48V – Standby Mode: The controller is turned "on" while other subsystems are turned "off” Instrument will transition to standby on power up or when certain faults occur during operation – Receive-Only Mode: All electronics subsystems are powered on. However, the transmitter amplifier or the traveling wave tube amplifier(TWTA) will be in the off-state – Wind Observation Mode: This mode is to operate the instrument to continuously acquire data during the mission period – Calibration Mode: This mode is for the extended test of instrument gain parameters and monitoring of external interfering noise. A secondary objective is to further verify the performance of the instrument through selected self-tests The release of the V-camp and activation of antenna rotation are performed by separate commands, not as an instrument mode

22. ISS RapidScat Ops TIM22 11 December 2012 Commands (Design trades and decisions are in process) – Power – Digital Interface Board – Instrument commands Telemetry Data – Science Telemetry Instrument operating mode, status, error codes, time, etc. Backscatter measurements Calibration measurements Azimuth position measurements Includes engineering data from all subsystems – Health and Status Operating mode Valid and invalid command counters Error codes Subsystem temperatures, currents, status Ancillary Data – Predicted Ephemeris (TOPO/JSC) – As-flown Trajectory and Attitude (MSFC) Command & Telemetry Data

23. ISS RapidScat Ops TIM23 11 December 2012 RapidScat-EPF (APM) Electrical Interfaces PCU and DIB are add-on [to CDS] assemblies designed to bridge inherited hardware, which was designed to interface with spacecraft, to the ISS-EPF interfaces and as gateway to provide inhibit control and monitoring PCU and DIB will provide required payload health status to XCMU per ICD The DIB also addresses payload science data buffering, buffering up to two-day worth of science data. Power/data interfaces will be through standard CEPA provisions and will be designed

24. ISS RapidScat Ops TIM24 11 December 2012 RapidScat-EPF (APM) Electrical Interfaces PPSB XCMU PEHG US P/L Bus(1553) CEPA-PFRAM-CEPA PDU1 PDU2 J05 J03 J04 J06 Feed 1 Feed 2 US P/L Bus Stub 1 Prime Power 120VDC Survival Heater Power 120 VDC Cmd/HK Data Science Data 40kbps/CCSDS US P/L LAN-2 P05 P03 P04 P06 CDS SAS SES APM EPF SDX SSMB PCU DIB CDS I3: 120 V PWR C3: XCMU M3:XCMU I2: 48V PWR C2: DIB M2: XCMU I1a: V-band Release I1b: Spin I1c: RF C1: DIB-CDS M1: DIB-CDS Instrument Power 120V on/off (I3) Survival Heat 120V on/off Instrument Power 120V Relay Monitor (M3) Secondary Voltage 48V Relay Monitor (M2)

25. ISS RapidScat Ops TIM25 11 December 2012 Potential Hazard Identification HazardPossible Controls 1. RF radiation Inadvertent exposure of equipment or personnel Maintain a keep-out zone during operation during ground ops Shutdown during scheduled vehicle or EVA/EVR activity near keep-out zone Three independent inhibits prevent inadvertent radiation 2. ElectricalHigh voltage circuits are contained within a housing (e.g., TWTA high voltage power supply) 3. Stored energy devices (Retained) V-band Clamp: Antenna spin mechanism is clamped V-band capture mechanism is in place to prevent on-orbit debris Three independent inhibits prevent inadvertent release 4. Rotating structure Reflector Stop rotation in the event of EVA/EVR Three independent inhibits prevent inadvertent rotation 5. Pinch points & EntanglementsMeet standard EVA/EVR design practices Shields for heritage hardware will be added Clearly defined EVA keep-out zones 6. Structural failure during launchMeet structural design safety factors 7. Structural failure during operation Meet structural design safety factors

26. ISS RapidScat Ops TIM26 11 December 2012 Inhibits for Hazardous Functions 26 M1 M2

27. ISS RapidScat Ops TIM27 11 December 2012 Ground System Data Flow and Functions

28. ISS RapidScat Ops TIM28 11 December 2012 RapidScat Architecture and Data Flow RapidScat Scatterometer RapidScat Scatterometer MSFC ISS Operations @ Payload Operations Integration Center WSC S-band (Inst Cmd & HK) JPL provides Ku-band (Inst. Data) “Regular” updates to OD “Regular” updates to ISS attitude ~40 Kbps instrument data production rate ~0.5 GBytes per day generated Storage Capacity - 2 GBytes (4 days) 2 kbps forward Science via Ethernet Cmd/H&S Tlm on 1553 bus International Space Station JSC MCC-H TDRS = Tracking & Data Relay SatelliteOD = Orbit Determination NOAA = National Oceanic and Atmospheric Administration HK= HouseKeeping (i.e. engineering TLM) JAXA = Japan Aerospace Exploration Agency DAAC = Distributed Active Archive Cntr WSC = White Sands ComplexMSFC= Marshall Space Flt Cntr TDRS P/L Table updates P/L Data 300 Mbps via TDRSS Payload Operations & Planning Science Data Processing JPL – RapidScat Operations Center L0, L1, L2 products P/L Data Acquisition NASA Physical Oceanography Distributed Active Archive Center (PODAAC) Power/Analog Tlm via COLUMBUS EF (SDX ) ISS Activity Plan, Ephem. Predicts ESA Col-CC Data from Columbus XCMU Processed telemetry

29. ISS RapidScat Ops TIM29 11 December 2012 PD Ops Functional Block Diagram JPL Payload Monitoring MSFC HOSC/ POIC Payload Command Request(s) Freq: Once per day Range and Doppler Table Update Request(s) Freq: Once per day NASA Physical Oceanography Distributed Active Archive Center (PODAAC) Data Acquisition, Ingest, Format Weekly Look-ahead Plan Freq: Once per week Predicted Ephemeris and ISS Attitude Parameters Freq: Once per two days Broadcast Ancillary Data Freq: Once per orbit(?) ISS Clock to UTC Sync Freq: Once per day (?) Health and Safety Telemetry Freq: Once per orbit (?) Instrument Science Data Freq: Once per orbit (?) As-Flown Ephemeris and Attitude Freq: Once per orbit (?) Science Data System Preproc L0 – L1B Preproc L0 – L1B Process Control & Data Mngmnt Process Control & Data Mngmnt Level Proc L1B – L2A – L2B Level Proc L1B – L2A – L2B Cmd, Table Generation L0, L1, L2 Science Products Payload Operations & Planning RapidScat Operations Center Command DB Updates JSC

30. ISS RapidScat Ops TIM30 11 December 2012 JPL – RapidScat Ops Center Functions (1 of 2) Generate Commands – Send command requests with needed parameters/tables to POIC to implement using procedures and command database – Generate parameters, range and Doppler tables as needed Acquire and Process Payload Data – Acquire instrument data from HOSC-POIC Assume open internet; instrument packets including CCSDS header Files at ~ 1/rev granularity File interface is TBD – push/pull; notification/acknowledgement mechanism? – Previous I/F was FX/FastCopy – Preprocess instrument telemetry and ancillary data to forms of QuikSCAT to allow reuse of processing system Cleaned telemetry (instrument frames) L0B Ephemeris data Attitude data Time Correlation data – Process and evaluate instrument telemetry Standard processing produces L1a’ file(s) for Engineering Analysis (EA) – Process Science data to standard scatterometer products Process through levels L0B -> L1A -> L1B -> L2A -> L2B Deliver L1B, L2A, L2B to PODAAC for distribution to science community

31. ISS RapidScat Ops TIM31 11 December 2012 JPL – RapidScat Ops Center Functions (2 of 2) Acquire and Process Ancillary Data – Acquire ancillary data from TBD sources Assume open internet Ephemeris – predict (JSC, period covered?), determined (Accuracy, latency?) Attitude (period covered? Accuracy, latency?) Time Correlation (need to time tag instrument measurements to ~1 msec accuracy) – BAD is received onboard but not included in instrument telemetry – 1553 broadcast time is paired with instrument timer and included in telemetry ISS Operations Plan (JSC, period covered, updates?) – Evaluate need to update instrument tables based on activities, predicted orbit Generate instrument Range & Doppler tables with predicts Generate processor X-factor tables consistent with instrument tables

32. ISS RapidScat Ops TIM32 11 December 2012 Concept of Operations Highlights

33. ISS RapidScat Ops TIM33 11 December 2012 Mission Phases Mission PhaseDuration Prelaunch Integration and TestTBD LaunchTBD Installation9 hours Activation and Checkout2 weeks Preliminary calibration/validation (cal/val)2 weeks Science Operations (including long-term cal/val)24 months De-installationTBD DisposalTBD

34. ISS RapidScat Ops TIM34 11 December 2012 RapidScat Payload Operations Health and Status telemetry will be processed at POIC, verified per PDL and displayed to operators – Operators will notify JPL of telemetry alarms and anomalies Science telemetry will be archived at POIC – No POIC processing is necessary – JPL will pull files from POIC (once an orbit is preferred frequency) Science data telemetry will be processed at JPL typically one orbit at a time – Engineering telemetry is included and processed with science packets for routine health checks and trending – Blocks of science data products (3-4 days at a time) complete quality checking and are delivered to the PODAAC at JPL for archiving and distribution Plan for a daily command sequence to upload operating tables to RapidScat – JPL will develop tables based on ISS ephemeris and attitude predicts – POIC will issue commands to upload those tables Instrument level fault protection will transition instrument to safe state (typically standby mode with RF transmission disabled) – There is no apparent need to implement ISS level autonomous responses to instrument conditions POIC and JPL will plan for special RapidScat operations as required by ISS for EVA or vehicle approaches – Inhibit RF and rotation as required by flight rules – POIC will coordinate with COL-CC when commanding to the Columbus SDX XCMU is necessary Response to Instrument Anomalies – Instrument team at JPL and POIC will collaborate to investigate anomalies – Specific recovery process along with any new procedures will be provided by the JPL Instrument team – POIC will issue commands

35. ISS RapidScat Ops TIM35 11 December 2012 Berthing/EVR Installation Two-Step Installation Sequence: Step 1 Install Nadir Pointing Adapter to SDX RapidScat in Dragon Trunk berthed at Node 2, in the presence of HDEV on SDN site Two-Step Installation Sequence: Step 2 Install Instrument to Nadir Pointing Adaptor SpaceX carries RapidScat as two standard FRAM- based units to berth at Node 2; PD power off but survival heaters on With HDEV at the SDN site, sufficient clearance to install RapidScat in two sequential steps, first install Nadir Pointing Adapter to SDX then the Instrument to the Adapter (sequences shown); also sufficient clearance to access HDEV Alternate sequence being considered: Put Instrument on EOTP, install Nadir Pointing Adapter to SDX, retrieve Instrument from EOTP and install onto the Adapter

36. ISS RapidScat Ops TIM36 11 December 2012 Instrument Power On Sequence POIC coordinates commanding from Col-CC as required to operate resources at Columbus SDX Instrument subsystems are powered on sequentially DIB subsystem is powered first via 120 V power feed at Columbus SDX and then via XCMU discrete commands – The instrument power converter comes on – Survival heaters are powered from the 120 V power feed – Thermal safe heaters are powered from the instrument PCU secondary voltages – Establishes communication on the 1553 interface to PL MDM – MRDL interface is on but not transmitting science data – DIB begins receiving instrument commands, broadcast time and BAD from PL MDM and supplies Health and Status data over the 1553 bus The remainder of the instrument power on sequence is handled from POIC (ESA Col-CC commanding is not necessary for the remainder of the process) CDS is powered by ground command via pulse discrete commands sourced by DIB – Science data transmission begins on the MRDL – Instrument Pulse Repetition Frequency (PRF) clock is temporarily provided by CDS V-band is released via 1553 bus command to DIB to operate the V-band separation nut

37. ISS RapidScat Ops TIM37 11 December 2012 Instrument Power On Sequence SAS is powered on to 18 rpm rotation rate via 1553 bus commands to DIB which in turn controls relays – Spin up requires 5 minutes SES is powered on via 1553 bus commands to DIB to control relays – PRF clock from SES takes over from CDS PRF clock and now controls system timing The SES supplemental heater relays are commanded to enable the heater via 1553 bus command to the DIB which is passed through to CDS to control the power relays – SES Supplemental heater can only be disabled AFTER SES AND TWTA are powered on TWTA is powered on via 1553 bus command to the DIB which is passed through to CDS to control the power relays – TWTA high power voltage supply requires 3 minutes to transition to standby mode All instrument systems are now operating in standby mode – The TWTA does not transmit any RF energy through the antenna – Instrument operational parameters can be set to desired values and table uploads can be accomplished

38. ISS RapidScat Ops TIM38 11 December 2012 Description of Instrument Check-out Functional verification of all subsystems – Command and data paths and functionality – Spin mechanism health and status – Scatterometer receiver characteristics – TWTA health, drive power level and output power – Transition through all operating modes Wind Observation Mode parameter set-up – Parameter selection, response and analysis of science data iterated as required to optimize performance – Range and Doppler table generation and uploads as required to support the set-up and verification process

39. ISS RapidScat Ops TIM39 11 December 2012 Comments

40. ISS RapidScat Ops TIM40 11 December 2012 Comments Operations considerations: – Keep it simple and low cost for both ISS and ESD – Facilitate science and potential operational capabilities if possible Want to understand what options we have relative to simplicity, cost and adaptability. Would like to define responsibilities, deliverables and schedule milestones (next page) – High level now (for PIM schedule); more detail by early January as design trades become final Identify topics and plans for subsequent meetings

41. ISS RapidScat Ops TIM41 11 December 2012 Deliverables