24-1MAVEN IPSR October 30,31, 2012

Particles and Fields PackagePre-Ship Review

October 30,31, 201224: ATLO Support

Dave Curtis

Mars Atmosphere and Volatile EvolutioN (MAVEN) Mission

24-2MAVEN IPSR October 30,31, 2012

Post Delivery Support

• PFP ATLO team consists of:– Dave Curtis, Systems, Package Manager– William Thompson (LASP), Systems, LPW/EUV, Local– Tony Mercer, Test Conductor– Paul Turin and Instrument Mechanical leads for mechanical operations– Dorothy Gordon, PFDPU lead, for electrical integration– Millan Diaz-Aguado, Thermal (esp. Thermal Vac)– Tim Quinn, GSE– Jorg Fischer, Chris Scholz, QA– MAG Team to support Magnetics Tests– Instrument leads will support critical testing

• William Thompson is local and can be on the spot on short notice; the rest of the team will be available as needed– Will will be trained to monitor the package during Self-Test and SVT

• Telemetry data will be available in real time at Berkeley for critical tests, reducing the need for large numbers of team members at ATLO– PFP GSE supports this

• Critical tests (CPT, EMC, Thermal Vac) will have extra team support

24-3MAVEN IPSR October 30,31, 2012

ATLO On-The-Floor Support

• PFP Team Members will be on the ATLO floor to support:– Instrument Installation / Removal– LPW Whip Installation / Removal– SEP Sun Shade Installation– EGSE Stimulus Operation during functional tests

• SEP Radiation Source• LPW Stimulus Rack• EUV Stimulus

– Red Tag Cover Installation / Removal– HV Enable Plug Installation / Removal– Pin-Puller stow– LPW Restraining Pin Removal

24-4MAVEN IPSR October 30,31, 2012

ATLO GSE

• Both MSA and SOC can display PFP housekeeping• PFP GSEOS computer will be at LM for local display of

data• Telemetry also available remotely in near real time for

extended team support for Critical Tests• On-the-floor GSE includes (per ICD):

– LPW stimulus rack– SEP radiation source– EUV lamp– EUV hall effect sensor– MAG shield cans, test harness– MAG test magnetometers (for compatibility test, swing test)– Actuator reset tool, SEP flexure clamps, SEP handle– Red-tag covers, LPW deployment restraining pins

24-5MAVEN IPSR October 30,31, 2012

Red-Tag, GSE Usage in ATLO

Description Type

I nstrument Transport

(1)I nstrument

I nstall S/ C I &T CPT SVTS/ C EMI /

EMCS/ C

AcousticS/ C

Vibration S/ C T-Vac MagneticsMass

Properties

S/ C Transport

(1)

S/ C Shipment to Launch

Launch Site Flow

Prior to LV

encapsulation

MAX Protect

SEP 1 HandleON ON OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF

SEP 1 SunshadeOFF OFF ON ON ON ON ON ON ON ON ON ON ON ON ON ON

SEP 2 HandleON ON OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF

SEP 2 SunshadeOFF OFF ON ON ON ON ON ON ON ON ON ON ON ON ON ON

SEP1 Aperture Covers - Qty. 4 Hard ON ON OFF OFF OFF OFF OFF OFF OFF ON OFF ON ON ON OFF ON

SEP2 Aperture Covers - Qty. 4 Hard ON ON OFF OFF OFF OFF OFF OFF OFF ON OFF ON ON ON OFF ON

STATI C Cover Hard ON ON OFF OFF ON OFF OFF OFF OFF ON OFF ON ON ON OFF ON

SWEA Cover Hard ON ON OFF OFF ON OFF OFF OFF OFF ON OFF ON ON ON OFF ON

SWI A Cover Hard ON ON OFF OFF ON OFF OFF OFF OFF ON OFF ON ON ON OFF ON

LPW Whip Protector/ Stimulus – Qty. 2 Hard OFF OFF OFF ON OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF

LPW No-whip cover - Qty 2 Hard ON ON ON OFF ON OFF OFF OFF OFF OFF OFF ON ON ON OFF ON

LPW Test Whip - Qty 2 OFF OFF OFF ON OFF ON ON ON ON OFF OFF OFF OFF OFF OFF OFF

LPW Flight Whip - Qty 2 OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF ON OFF

STATI C High Voltage Enable Plug OFF OFF OFF OFF OFF OFF OFF OFF ON OFF OFF OFF OFF OFF ON OFF

SWEA High Voltage Enable Plug OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF ON OFF

SWEA Tvac HV Enable Plug OFF OFF OFF OFF OFF OFF OFF OFF ON OFF OFF OFF OFF OFF OFF OFF

SWI A High Voltage Enable Plug OFF OFF OFF OFF OFF OFF OFF OFF ON OFF OFF OFF OFF OFF ON OFF

Purge (SWEA, SWI A, STATI C, EUV)Purged & Bagged

OFF ON ON ON ON OFF OFF OFF ON ONPurged & Bagged

ON ON ON ON

Purge Bag Soft OFF OFF ON OFF ON ON OFF OFF OFF ON ON ON ON ON OFF ON

Sacrificial Purge Bag and/ or Crate Soft ON OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF ON OFF OFF ON

Other

EUV Removable Optical Alignment Cube ON ON OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF ON OFF

EUV Hall Effect Sensor OFF OFF ON ON ON OFF OFF OFF ON OFF OFF OFF OFF OFF OFF

LPW Restraining Pin - Qty. 2 ON ON ON ON ON ON ON ON ON ON ON ON ON ON OFF ON

MAG Sensor On Array OFF OFF OFF ON ON ON OFF ON ON OFF OFF ON OFF

MAG Sensor on Deck ON OFF ON OFF OFF OFF OFF OFF OFF ON ON OFF ON

MAG Sensor on array stub OFF OFF OFF OFF OFF OFF ON OFF OFF OFF OFF OFF OFF

MAG Sensor in GSFC Shield Can OFF OFF OFF ON OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF

LPW Stim Rack OFF OFF OFF ON OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF OFF

Cover/ Purge State (ON/ OFF)

24-6MAVEN IPSR October 30,31, 2012

Pre-Integration Bench Test

• On arrival at LM the PFP shall be bench-tested prior to integration

• LM shall provide facilities to support bench testing– Clean room– Purge gas provided– Adequate Bench space provided– Power provided– SSL provides instruments, EGSE, MGSE, purge manifold, test

plans

• Will perform a CPT to ensure instrument survived shipping and is ready to integrate

• LM will hold a review prior to integration to verify readiness

24-7MAVEN IPSR October 30,31, 2012

PFP Testing on the Spacecraft

• PFP tests consist of:– Comprehensive Performance Test (CPT)

• Performed right after integration and again after environments• Includes external stimulus for SEP, LPW, EUV, MAG• ~1-2 days

– Limited Performance Test (LPT)• Part of Spacecraft ‘Self Test’ performed between environments, after moves,

etc.• No external stimulus• ‘Test Copper’• ~1-2 hours

– System Verification Tests (SVT)• Simulates mission events, such as science orbit

• PFP team has provided test scripts to LM for these tests and is working with LM to convert and verify those scripts and match them to the test cases

• LM is aware of PFP test constraints, such as no high voltage outside of vacuum– High voltage enable plugs shall be removed to prevent accidental HV

turn on.

24-8MAVEN IPSR October 30,31, 2012

Post Spacecraft Environment Test

• SWEA, SWIA, STATIC functionality cannot be assessed outside a calibration chamber– HV can’t be operated in air– Need electron/ion guns to verify detectors, electrostatic optics,

foils• There is a spot in the ATLO flow after environments for

SWEA, SWIA, STATIC to be removed from the spacecraft and returned to SSL for test– Need a few weeks at SSL to run the three instruments through

the calibration chambers.– A subset of the calibrations previously run– Use the same shipping arrangements used to get them to ATLO– Post-re-integration functional test– Current plans allow this to be completed at LM

• This has been the baseline since the before PDR– Supported by LM ATLO planning