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X-Ray Gratings Mission. Mission Systems Rud Moe Theo Bugtong Frank Kirchman 19 – 23 March, 2012. X-Ray Grating Mission Requirements (from customer). X-Ray Grating Mission Requirements, cont’d. X-Ray Grating System Design Overview. Mechanical

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x ray gratings mission

X-Ray Gratings Mission

Mission Systems

Rud Moe

Theo Bugtong

Frank Kirchman

19 – 23 March, 2012

x ray grating system design overview
X-Ray Grating System Design Overview
  • Mechanical
    • 8 Sided Gr-Ep S/C structure surrounding primary mirror
    • Lower deployable SA to match CP to CG and provide sunshade
  • Thermal
    • Sunshades to accommodate +25, -45 Pitch angle
    • Cold bias baseline with heater control
  • Propulsion
    • Mono prop system for orbit maintenance and momentum unloading, 12 thrusters
  • Attitude Control
    • Star trackers (2 heads, redundant processor), SIRU (internally redundant), sun sensors (8) for determination
    • Momentum wheels (4) for control
  • Communications
    • Two DSN S/Ka-band transponders
    • Two 10 watt Ka-band TWTAs
    • Gimbaled 0.5 M dual frequency high-gain antenna
    • DSN 34m antenna
  • Power
    • 6.7 m2 SA
    • 28V bus
    • 100 AH battery
x ray grating system design overview cont d
X-Ray Grating System Design Overview, cont’d.
  • Avionics
    • Build to print system
    • Primary C&DH System with Cold Backup system
  • SW
    • High heritage reuse
    • No challenging requirements for Xray Grating
  • I&T
    • GSFC facilities baselined
    • MSFC XRCF consideration for optical verification
  • Ops
    • COTS/GOTS MOC baselined
  • Reliability
    • Class B
  • Launch Vehicle
    • Falcon 9
  • Orbital Debris
    • No specific disposal method required
  • Flight Dynamics
    • Standard L-2 halo or Lissajous
x ray grating communications functional configuration
X-Ray Grating CommunicationsFunctional Configuration

decrypter

S

S/Ka-band

Transponder

Diplexer

Hybrid

S

S-Band omnis

PA

SWITCH

K

S

decrypter

S

C&DH

Diplexer

PA

S

SWITCH

S/Ka-band

Transponder

S

Hybrid

SWITCH

ISOLATOR

Ka-band

TWTA

SWITCH

S / Ka

HGA

Triplexer

K

Ka-band

TWTA

x ray grating program flow
X-Ray Grating Program flow

Mission

Critical Design

Review (CDR)

9/28/2018

Phase B

Start S/C Bus

8/8/2016

Preliminary Design

Review (PDR)

9/1/2017

S/C Bus

Contract

Award

System

Definition

Review (SDR)

Project

Start

8/8/2014?

Phase A

Preliminary Analysis

Phase B

Definition and Prelim Design

Phase C

Final Design

Preliminary

Design

Mission

Definition

System

Definition

Final

Design

11 months

24 months

13months

Transition To Nominal Ops 7/11/2021

End of

Primary Mission

3/15/2024

Instrument

Delivery

2/1/2019 4/10/2020 5/8/2020

Launch

6/11/2021

Ship

2/26/2021

Funded

Reserve

Phase D-1 Subsystem Development, S/C Integration & Test, Launch Prep

Phase E/F

Operations

Phase D-2

Launch & Checkout

Funded

Reserve

Fab., S/C Assy & Func. I&T

~16mo.s

Prep for Launch

~3mos

Obser. I&T

9.5mo.s

Cruise, Orbit Insertion

& Checkout

PrimaryMission

Reserve

7 mo.s

Launch &

Checkout

Extended Mission ?

29months

7months

1 month

2mo

33 mo

Timeline not to scale

x ray grating systems implications for cat configuration
X-Ray Grating – Systems Implications for CAT configuration
  • CAT instrument potential system-wide impacts and implications
    • Instrument Mass reduced to 84.5 kg
      • Structure mass
        • Fuel mass
        • Thrusters size
      • Inertia
        • Attitude Control torquers size
      • CG
        • CP-CG shield position
        • Thrusters alignment
    • Instrument Power reduced to 85 W (affects power and thermal)
      • Solar Array size
      • Battery DOD or size
      • Thermal load
        • Radiator sizes
    • Avionics TT&C and FSW specifics
    • System interaction impacts not fully assessed
x ray grating issues considerations
X-Ray Grating Issues/Considerations
  • Tracking required for 1 msec absolute timing
    • Reaction wheels sized for 1-month momentum management cycle
    • 21-day nonpropulsive tracking arc may possibly be shortened
    • Portion of timing error allocated to position uncertainty is TBD
    • Pitch pointing produces CP-CG offset and solar pressure momentum accumulation, and may require more frequent momentum management
    • Momentum management with coupled thrusters produces a small contribution to position delta-V
    • Position uncertainty also influences station-keeping delta-V
    • Arrangement of target pointing sequence may help balancesolar pressure momentum accumulation
  • Aperture cover mechanism versus safehold solar pointing reliability
    • Aperture cover is jettisoned; recloseable cover is not baselined
    • Increased reliability of safehold solar pointing may be more cost effective and reliable than a recloseable cover
x ray grating future work
X-Ray Grating Future Work
  • Weight-optimized configuration
  • Reconfigured Payload configurations
    • Extensive redesign needed to reach smaller LV accommodations
  • Attitude determination analysis
    • Error budgets
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