X ray gratings mission
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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

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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 mission requirements from customer

X-Ray Grating Mission Requirements (from customer)


X ray grating mission requirements cont d

X-Ray Grating Mission Requirements, cont’d.


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 mass

X-Ray Grating Mass


X ray grating mission timeline

X-ray Grating Mission Timeline


X ray grating ops concept

X-Ray Grating Ops Concept


X ray grating observatory concept

X-Ray Grating Observatory Concept


X ray grating s c block diagram

X-Ray Grating S/C Block Diagram


X ray grating power

X-Ray Grating Power


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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