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Systems Engineering. Systems Agenda. Design Mission Description Instrument and Probe Configuration Launch and Mission Description Requirements Verification Summary, Waived and Pending Requirements New Mission Profile Review Resources Operating Hours Problem Failure Reports

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Systems agenda
Systems Agenda

  • Design

    • Mission Description

    • Instrument and Probe Configuration

    • Launch and Mission Description

  • Requirements Verification

    • Summary, Waived and Pending Requirements

    • New Mission Profile Review

    • Resources

    • Operating Hours

  • Problem Failure Reports

    • Statistics and Status

    • Unverifiable Failures

    • Operational WorkArounds


Mission summary
Mission Summary

Launch

Vehicle: Delta II, Eastern Range

Apogee: 91845.2 km ± 9567 km

Perigee: 435 km ± 10 km (500 km ± 7 km on or after 3/1/2007)

Inclination: 16.0 deg ± 0.5 deg

Date: February 15, 2007

Space Segment

Spacecraft: 5 Spinning Probes with Fuel for Orbit & Attitude Adjust

Instruments: 3-Axis Electric Field, Magnetic Field

3-D Ion & Electron Particle Detectors

Spin Rate: 20 RPM

Orbit Period(s): 1, 2 and 4 days

Orientation: Ecliptic Normal

Ground Segment

Observatories: 20 Northern with All Sky Imagers and Magnetometers

Control Facilities: Mission and Science Operations Centers

Operations

Phases: L&EO, Cruise, Ascent, Campaigns, De-orbit

Lifetime: 2.3 years


Instrument configuration
Instrument Configuration

IDPU: Instrument Data Processor Unit

SPB : Spin Plane Booms (4x)

AXB : Axial Booms (2x)

SST : Solid State Telescope (2x)

ESA : Electrostatic Analyzer

FGM : Fluxgate Magnetometer

SCM : Search Coil Magnetometer


Probe configuration
Probe Configuration

Antenna

EFI Axial Booms (2, Stowed)

ESA

Miniature Sun Sensor

Fuel Tank

IDPU

EFI SPB

Repress Tank

Transponder

Fuel Tank

Thruster A2

Thruster T1

EFI SPB

Thruster A1

BAU

Battery

Gyros

EFI SPB

Thruster T2

AEB


Launch configuration
Launch Configuration

  • Dedicated launch accommodated within standard Delta 7925-10 vehicle configuration and services

  • 10’ Composite Fairing required to accommodate five Probes on the Probe Carrier in the “Wedding Cake” configuration

  • PC stays attached to Delta 3rd stage after probe dispense

  • Each probe dispense from the PCA is coordinated with but independent of the other probes

  • No single probe anomaly precludes dispense ofremaining probes

Standard Delta 10 ft. Fairing Static Envelope

Probe Carrier Assembly

(PCA = 5 Probes + Probe Carrier) on L/V

3712 PAF

Star 48 3rd Stage

Probe Carrier Assembly (PCA) on Delta 3rd Stage

THEMIS Launch Configuration



Requirements status
Requirements Status

  • Mission Requirements Documentation (MRD)

    • THM_SYS_001K_MRD.xls

  • Mission Requirements Verification

    • 476 Requirements total

    • 467 Requirements verified

    • 5 Requirements pending

    • 4 Requirements waived


Requirements waived
Requirements Waived

  • Implementation Change

  • IN.ESA-08: ESA Dayside Energy Flux Attenuator

  • Waived: Electronic Counting Was Fast Enough

  • IN.DPU-09: Stored Housekeeping Telemetry Storage

  • Waived: BAU saves all IDPU Engineering Data

  • As Measured

  • IN.EFI-11: EFI Noise Level < 1x 10^-4 mV/m/sqrt(Hz).

  • Waived:EFI measured noise level is 2 to 3 x 10^-4 mVm/sqrt(Hz).

  • PC.Mech-1: Probe-to-Probe Static Clearance of 4 inches

  • Waived: Current static clearance is 3.75 inches.


Requirements pending
Requirements Pending

  • Launch Site Verification

  • M-33 Electrostatic Cleanliness requirement verification pending ESC survey after all flight close-outs (Jan 9)

  • M-45, M-47, PC-8 PCA Mass Properties (Mass, CG, and Principle Misalignment) requirement verification pending PCA Spin Balance Test and final weighing of PCA with fueled Probes. (Jan 12 and 13)

  • Post-Launch Verification

  • IN.ESA-13 ESA On-Orbit Calibration requires raw data to be collected prior to final coefficients to be delivered to the Science Operations Center. (March 2007)


New mission profile
New Mission Profile

  • Mission Profile Review for Feb 15, 2007 Launch

    • EFI Boom Deploy delayed ~ 9 months on Probes 1 & 5

      • THEMIS Deployment Motors Life Test (21 mo @ 50 C)

      • CLUSTER lifetime tests also relevant and showed no issues

    • RCS Re-pressurization delayed about 6 months

      • No Issues with RCS Components

      • Cassini waited several years to do the recharge.

    • Ascent Maneuvers Delayed appx 6 months

      • Increased IRU radiation qualification to 63 Krad (RDM of 2)

    • Power considerations

      • Improved launch orientation, side solar arrays in sun.

      • No change in number or duration of eclipses

    • Thermal environment

      • No change


Resources
Resources

  • Mass Status

    • < 2% mass deviation between Probes (requirement)

    • Dry Mass Margin: 4.5% (Worst case)

  • Power Status

    • Probe CBE: 38.7 W

    • Probe Capability: 40.60 W

    • Probe Margin: 8.8% (First 3-hour Eclipse Season)

      4.9% (Second 3- hour Eclipse Season)


Operating hours
Operating Hours

  • Integrated Probe Hours:

  • Components : Averaged 780 hours run time prior to integration.

  • Failure Free Hours: Hours accumulated on core system after return of transponder and BAU during mission integration.

  • Late Instrument Swaps (>100 hours gained on integrated system after all swaps):

    • Spare SST on F1 swapped in prior to TVac in August

    • Spare SCM on F1 swapped in early October

    • EFI re-work on F1-F5 completed in November

  • Thermal Vacuum Hours: 120-150 failure free hours were accumulated on all components during Probe Level TVac. Components accumulated and average of 250 hours during Component Level TVac.


Problem failure reports
Problem/Failure Reports

  • PFR Statistics (All Spacecraft)

  • Total : 237

  • Closed : 237

  • Open : 0

  • Unverifiable Failures : 13

  • Operational Work-Arounds : 10




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