THEMIS SUITE PRE-ENVIRONMENTAL REVIEW 1 UCB May 2, 2005 THEMIS Pre-Environmental Review Instrument...

THEMIS SUITE PRE-ENVIRONMENTAL REVIEW 1 UCB May 2, 2005

THEMIS

Pre-Environmental Review

Instrument Verification Overview

Ellen Taylor

University of California - Berkeley


Requirement Development and Verification Process

Top-Level requirements developed during Phase A • Concept Study Report (CSR) provides basic mission concept• Outlines top-level requirements imposed by science and programmatic objectives

Mission requirements flowed down (to subsystem level), formalized and documented early in Phase B• All elements of CSR concept and mission requirements reviewed by development team• Mission Requirements Database (MRD) developed and reviewed• MRD finalized and put under Configuration Control at System Requirements Review

(SRR), July 2003

Subsystem Interfaces and Component Requirements further detailed in Phase B• Interface Control Documents between Subsystems and Institutions• System and Subsystem Specifications (Board Specifications, SOWs, etc)• Mission Plans and Policies (PAIP, Risk Management Plan, FMECA, etc)• Control Plans (Magnetics, ESC, Contamination)


Requirement Development and Verification Process

Requirement Verification Plans developed in Phase B and C• Development of Verification Matrix ensures a test or analysis is scheduled for all Mission

Requirements in MRD• Performance Verification and Environmental Test Plans provide launch and space

environments and outlines comprehensive component, subsystem and system level test program

• Environmental Test Matrix (ETM) developed

Requirements Compliance and Verification Matrices completed in Phase D• MRD and ETM evolve into summary of verification and test program as run• Documents Verification and Compliance Status of all Requirements• Provides direct trace-ability from requirements to test procedures and reports


Performance Verification

Performance Verification Program• Applies to all technical requirements stated in MRD and associated documents• Each item in MRD has field for verification method

Performance Verification Methodology• Verification of requirements is by Inspection (I), Analysis (A), Test (T) or combination• Tasks for each method include: establishing the criteria; preparing plans and procedures;

implementing; and documenting the results.

Performance Verification Levels• Verification will be performed at one or more of following levels: Component, Sub-Assembly,

Assembly, Subsystem, System

Example from THEMIS MRD Verification Matrix:

Org. ID Title Statement Compliance Verification method

Mission Requirements (M-#)Lifetime and RadiationUCB M-3 Total Dose

RadiationTHEMIS shall be designed for a total dose environment of 33 krad/year (66 krad total)

GSFC Radiation analyses performed. Performance Assurance and Implementation Plan (PAIP) for part selection.

A: GSFC Ray Trace Radiation Analysis provides radiation environment for every subsystem and instrument; I/T: Parts selected with known radiation characteristics or total dose radiation tested

Mission DesignUCB M-12 Orbital Plan The selected orbital plan shall achieve greater

than 188 hours of five-probe conjuctions per year during the prime tail observation season

Compliance per Conjunction Analysis A: Conjunction analysis


MRD Status

Mission Requirements Document (MRD) Status• MRD Rev A released at System Requirements Review (SRR)

• MRD Rev B released prior to Instrument and Subsystem Peer Reviews

• MRD Rev C released at Mission PDR

• MRD Rev D released during Instrument and Subsystem Peer Reviews• Incorporated MPDR RFAs and System Change Notices (SCNs) since PDR

• Added compliance and detailed verification plan (I/A/T) for each requirement

• MRD Rev E released at Mission CDR

• MRD Rev F will be released at Mission PER• Working version of Rev F is used to track verification status of all requirements

• Most Instrument performance requirements have been verified during the ETU development and test w/ all instruments meeting or exceeding required performance

• One waiver is expected for Instrument requirements – SST exceeds magnetic budget allocation


Environmental Verification

Environmental Test Program• Instrument hardware is tested to environmental requirements using GEVS as a Guideline per

CDRL THM-SYS-005 THEMIS Instrument Payload Verification and Environmental Test Specification and summarized in Environmental Test Matrix (ETM)

Environmental Test Methodology• Each hardware item in ETM has fields for test description, test date, and procedure/report• Applies to all instrument assemblies, subsystems and systems

Example from THEMIS Environmental Test Matrix as-runs:


ETM Status

Environmental Test Matrix (ETM) Status• ETM presented at Mission CDR and delivered to GSFC as CDRL

• ETM has been further reviewed with minor changes to overall plan• Temperature updates to the Instrument and Instrument Suite Level based on thermal

modeling refinements, add strength test to AXB carbon tube

• ETM has evolved into summary of test program as-run• Working version is used to track test status of all instrument systems

• Most Instruments have successfully completed all environmental tests on FM1 units

• FM1 Mag Booms have not finished Thermal Vacuum Testing – expected mid May

• FM1 ESA has not gone through Thermal Vacuum Testing – will occur after suite TV


Environmental Test Matrix

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Instrument Payload 6 UCB T9 T10 T10 T10 T10 6 -30 to +45 -40 to +55 -40 to +55 M3 T14 1000 100 FGM Sensor 1 TUBS T T4 T5 A7 M1 T9 2 T -100 to +65 -57 to +8 -120 to +75 -120 to +75 T11 M2 A 100 A FGM Boom 1 UCB T T4 T5 A7 M1 T7 T9 2 T -35 to +45 -24 to +32 -45 to +50 -45 to +50 T11 M2 SCM Sensor 1 CETP T T1 A2 T4 T5 A7 M1 T9 2 T -65 to +45 -59 to +0 -70 to +45 -70 to +45 T11 M2 T SCM Pre-Amp 1 CETP T1 A2 T4 T5 A7 M1 T9 2 T -30 to +45 -18 to +38 -45 to +55 -45 to +55 T11 M2 T SCM Boom 1 UCB T T1 A2 T4 T5 A7 M1 T7 T9 2 T -35 to +45 -24 to +32 -45 to +50 -45 to +50 T11 M2 A 100 A ESA 1 UCB T1 A2 T4 T5 T6 A7 M1 T7 T9 2 T -30 to +45 -20 to +37 -40 to +55 -40 to +55 T11 M2 SST Sensor 2 UCB T1 A2 T4 T5 A7 M1 T7 T9 2 T -55 to +45 -50 to +12 -65 to +55 -65 to +55 T11 M2 A 100 A EFI Pre-amp 1 UCB T1 A2 T4 T5 A7 M1 T9 6 -125 to +80 -121 to +71 -135 to +90 -135 to +90 T11 M2 T A 100 A EFI SPB 1 UCB T1 A2 T4 T5 A7 M1 T7 T8 T9 2 T -20 to +40 -16 to +16 -25 to +50 -25 to +50 T11 M2 EFI AXB 1 UCB T1 T2 T4 T5 A7 M1 T7 T9 2 T -25 to +30 -13 to +14 -35 to +40 -35 to +40 T11 M2 IDPU Box 1 UCB T1 A2 T4 T5 A7 M1 T9 2 T -30 to +45 -18 to +39 -40 to +55 -40 to +55 T11 M2 T12 100 A Instrument Harness 6 UCB M4 T11 M2 T13 Instrument Blankets UCB A7 T11 M2 T13Probe Subsystems SAI T T T T A T T A M T T T T T 8 T M T A 1000 100 AProbe #1 1 SAI T T T T T T M T self self T T 4 T T M T 1000 100Probe #2-5 4 SAI T T A T T T M T self self simil simil 4 T15 T M T 1000 100Probe Carrier 1 SAI T T T T A A MProbe Carrier Assembly 1 SAI M

notes:T1 0.25g sweep from 5 Hz to 2000 Hz T10 Per MIL-STD-461C (levels in thm-sys-005) T2 AXB Tube gets Strength test (carbon fiber structure) T11 Grounding and ESC compliance checked for each component prior to integrationA2 Analysis to show margin on Yield at 2.0 x limit load; and Ultimate at 2.6 x limit load M2 DC Magnetics measured prior to Instrument Payload integrationT3 Test conducted at 1.25 x limit load M3 AC Magnetics measured in mag facility at Probe LevelT4 ETU tested to Qual; F1 tested to Protoflight; F2-F6 tested to Acceptance per SAI- M4 Mass onlyT5 ETU tested to Qual; F1 tested to Protoflight; F2-F6 tested to Acceptance (sine profile in thm-sys-005) T12 Total Dose and SEE Testing at part level if necessaryT6 ETU tested with SC shock test T13 60C for 48 hours prior to TV w/ integrated payloadA7 Analysis to show margin at 2 x maximum pressure differential (launch ascent profile in thm-sys-005) T14 Contamination Verification w/ TQCM during Instrument Payload Thermal VacM1 Mass, CG and MOIs measured T15 Limited Thermal balance on probes 2 through 5T7 At least 10 x number of actuations during the mission life, unless mechanism is on Limited Life Items ListT8 SPB Motor to go through Life Test - operation after 6 months (TBR) A AnalysisT9 Safe-to-Mate and compliance to ICD prior to Integration T Test


MRD Instrument Suite Requirements• Lifetime and Radiation• Resource Budgets• Thermal• Contamination• Interfaces• Test and Verification

Suite MRD Verification


Instrument Payload


REQUIREMENT VERIFICATION METHOD

IN-1. The Instrument Payload shall be designed for at least a two-year lifetime

I/A: All systems designed to two years and analyzed for two year mission

IN-2. The Instrument Payload shall be designed for a total dose environment of 33 krad/year (66 krad for 2 year mission, behind 5mm of Aluminum, RDM 2)

IN-3. The Instrument Payload shall be Single Event Effect (SEE) tolerant and immune to destructive latch-up

A: GSFC Ray Trace Radiation Analysis provides radiation environment for instrument;

I/T: Parts selected with known radiation characteristics or radiation tested for TID and/or SEE

Lifetime and Radiation

Table 2: Radiation dose levels on sensitive parts

Detector Name Box Wall Thickness

(mil) Phase 1 - All Probes

Dose (krad-Si) Phase 2 - Probe 5

Dose (krad-Si) Total Dose (krad-Si)

IDPU 120 1.99E+00 2.33E+01 2.53E+01 ESA Instr 140 6.73E+00 7.48E+01 8.15E+01

SST1 275 5.88E-01 8.15E+00 8.74E+00 SST2 275 6.13E-01 8.49E+00 9.10E+00 EFI 200 1.67E+00 2.05E+01 2.22E+01

Status• GSFC Radiation Analysis complete. See Table 2 from report below.

• Environment < 33 krad for all instruments except ESA (81.5 krad)• Additional electronics shielding added to ESA

• 100% Instrument Parts screened for TID/SEE requirements. Approx. 20 parts were tested.• No parts that failed radiation testing are being used• LVPS redesign required - reduced supply efficiency



IN-6. The Instrument Payload shall not exceed the total allocated mass budget in THM-SYS-008 THEMIS System Mass Budget.xls

T: Instrument payload will be weighed.

IN-7. No component of the Instrument Payload shall exceed the allocated mass budget in THM-SYS-008 THEMIS System Mass Budget.xls

T: Instruments will be weighed prior to delivery.

Resource Budgets - Mass

CBE: 24.15 kgAllocation: 24.63 kgContingency: 2.2%

Status• Approx. 98% of ETU Instrument Payload has been weighed

INSTRUMENT MASS

18.0019.0020.0021.0022.0023.0024.0025.0026.0027.00

Pha

se A

7/03

8/03

9/03

10/0

3

11/0

3

12/0

3

1/04

2/04

3/04

4/04

5/04

6/04

7/04

8/04

9/04

10/0

4

11/0

4

12/0

4

1/05

2/05

3/05

Date

Mas

s(kg

)

Instrument Allocation

Instrument CBE

Instrument Schedule



IN-8. The Instrument Payload shall not exceed the total power allocated in THM-SYS-009 THEMIS System Power Budget.xls

T: Instrument payload power will be measured.

IN-9. No component of the Instrument Payload shall exceed the power allocated in THM-SYS-009 THEMIS System Power Budget.xls

T: Instrument power will be measured prior to delivery.

Resource Budgets - Power

CBE: 15.26 WAllocation: 14.77 WContingency: -1.0%

Status• Approx. 90% of ETU Instrument Payload power has been measured (all Instruments except ESA)• ~3x power increase between ETU and Flight Actels was estimated and additional resistor load

put on 2.5V line for ETU system

INSTRUMENT POWER

11.00

12.00

13.00

14.00

15.00

16.00

17.00

18.00

19.00

20.00

21.00

22.00

Phase A 8/03 10/03 12/03 2/04 4/04 6/04 8/04 10/04 12/04 2/30/2004

Date

Po

wer

(W

)

Instrument CBE+Cont.

Instrument CBE

Instrument Schedule



IN-10. The Instrument Payload shall not exceed the allocated data budget of 750Mbits/orbit (uncompressed)

A/T: Analysis of data rates, data budget, system states over an orbit; analysis verified during functional/performance testing

IN-11. The Instrument Payload shall be capable of storing 1 orbit + 1 days worth of Instrument Science and housekeeping data.

A/T: Analysis of storage capability, FSW storage efficiency; analysis verified during functional/performance testing

Resource Budgets - Data

Status• 187.5MB storage is required (750Mbits/orbit +

1 day contingency = 1500Mbits = 187.5MB) • DCB contains 256MB SDRAM for TM storage.

Upper quadrant is devoted to ECC. • Memory analysis using predicted data rates

from Instruments show storage is sufficient for 4 day orbit + 1day contingency at worse-case spin period of 2.7seconds.

Mbytes Packets Raw EfficiencySurvey 105.3 70.5 67%Burst 43.4 30.5 70%Total 148.7 101.0 68%

96 hour Orbit Memory RequirementNominal 3 sec spin period


96 hour Orbit + 1 day Survey Memory RequirementNominal 3 sec spin period


96 hour Orbit + 1 day Survey Memory RequirementSpin Rate 10% high (2.7 sec period)



IN-13. The Instrument Payload shall survive the temperature ranges provided in the ICDs

A/T: Thermal analysis and modeling provides temperature predictions for Instrument Survival; Instruments are thermally tested to predicts plus margin

IN-14. The Instrument Payload shall perform as designed within the temperature ranges provided in the ICDs

A/T: Thermal analysis and modeling provides temperature predictions for Instrument Science Mode; Instruments are thermally tested to predicts plus margin

Thermal Requirements

Status• ETU Instruments are tested to Thermal Limits +10 degrees• Flight Instruments are tested to Thermal Predicts +10 degrees• FM1 Flight Instruments have completed Thermal Vacuum Testing, with the exception of:

• FM1 Mag Booms – TV not completed due to deployment problems. Will be completed following suite TV, as it needs the same facility.

• FM1 ESA – to be completed after suite TV. ETU ESA Pre-Amp was tested in IDPU TV Test. ETU ESA Actuator was tested in separate Release Plate Assembly TV Test.



IN-16 The Instrument Payload shall comply with the Magnetics Cleanliness standard described in the THEMIS Magnetics Cleanliness Plan

I/A/T: Verification assured by Magnetics Committee per component budget and requirements provided in THM-SYS-002 Magnetics Control Plan; Components measured prior to Probe Integration in Coil facility.

IN-17 The Instrument Payload shall comply with the THEMIS Electrostatic Cleanliness Plan

I/A/T: Verification per THM-SYS-003 ESC Control Plan; Analysis provides allowable resistance/area and insulator budget; Measurements are made at system level.

IN-18 The Instrument Payload shall comply with the THEMIS Contamination Control Plan

I/A/T: Verification per THM-SYS-004 Contamination Control Plan; Thermal Vacuum Bake-out planned w/ TQCM monitoring.

Contamination Requirements

Status• Worse-case offenders for Magnetics is EFI Motors, SST magnets, IDPU switching frequencies

• ETU EFI Boom motors w/ mu metal shielding tested at UCLA, meets budget of 0.25 nT @ 2m • SST Magnets analysis and testing show careful selection of magnets and pairing of sensors

can reduce the dc field at the FGM Sensor to within the allotted budget. Sensors do need to be mapped at earliest opportunity.

• IDPU frequency management plan has implemented in LVPS - switching frequencies above 100 kHz, separated by 10 kHz to avoid beat frequencies in science range. Compatibility testing with SCM verifies instrument power supply frequencies are outside science range.



IN-19. All Instruments shall comply with the electrical specifications

T: Requirements provided in THM-IDPU-001 Backplane Specification; interfaces verified during IDPU integration.

IN-20. The Instrument Payload shall be compatible per IDPU-Instrument ICDs

T: Instruments tested to ICD prior to delivery; interfaces verified during I&T of Instruments to IDPU

IN-21. The Instrument Payload shall be compatible per the IDPU-Probe Bus ICD

T: Instrument Payload tested to ICD prior to delivery; interfaces verified I&T of IDPU to Probe

IN-22. The Instrument Payload shall be compatible per Instrument-Probe Bus ICDs

T: Instrument Payload tested to ICD prior to delivery; interfaces verified during I&T of Instrument Payload to Probe

Interface Requirements

Status• All FM1 Instrument Boards (DAP, ETC, FGE, DFB, BEB) have been integrated and tested

with FM1 IDPU core system (LVPS, DCB and PCB)• All Instruments (SSTs, ESA, EFI Pre-Amp & Booms, FGM, SCM, Mag Booms) have been

integrated and tested with FM1 IDPU box (Core System and Instrument Boards)• Data Interface between IDPU and Probe BAU has been tested on 3 occasions (UCB-

Swales I/F Tests: July, October, December 2004). Various levels of interface verification completed during each test. Power Interface Test planned for January?

• Mechanical Hi-Fi Instrument Mock-ups provided to Swales for Integration to Hi-Fi Probe. Mass Models provided to Swales for Structure Strength and Thermal Testing.



IN-23 The Instrument Payload shall verify performance requirements are met per the THEMIS Verification Plan and Environmental Test Specification

I/A/T: Performance Requirements met as documented in MRD Verification Matrix

IN-24 The Instrument Payload shall survive and function prior, during and after exposure to the environments described in the THEMIS Verification Plan and Environmental Test Specification

I/A/T: Environmental Test Requirements met as documented in Environmental Test Matrix (ETM)

Suite Verification and Test

Status• As provided in MRD and ETM and summarized during Review:

• ftp://apollo.ssl.berkeley.edu/pub/THEMIS/1 Management/1.3 Systems Engineering/1. Requirements/thm_sys_001f_MRD.pdf

• ftp://apollo.ssl.berkeley.edu/pub/THEMIS/1 Management/1.3 Systems Engineering/1. Requirements/thm_sys_005AppA_InstrumentETM.pdf


Design Changes Since CDR

ORG. POC Doc Number Description StatusSystem Change Notices (SCN)UCB/Swales Ajulini/Taylor thm-scn-013 SCN 013 TLX System Signed-OffUCB/Swales Taylor/Ajulini thm-scn-014 SCN 014 No Quaternion Propogation On-board Signed-OffUCB/Swales Taylor/Ajulini thm-scn-015 Deleted because 15 deg is limiting case (SCN 015 10 deg Exclusion Zone)DeletedUCB/Swales Taylor/Ajulini thm-scn-016 SCN 016 Mass and Delta V Allocations Signed-OffUCB/Swales Taylor/Ajulini thm-scn-017 SCN 017 SPB Design Change (Stay Open Doors) Signed-OffUCB/Swales Turin/Brenneman thm-scn-018 SCN 018 Increase Instrument Mass Allocation 1kg Signed-OffUCB/Swales Turin/Brenneman thm-scn-019 SCN 019 Remove Pulse Train Thrust Capability Signed-OffUCB/Swales Turin/Brenneman thm-scn-020 SCN 020 Change Probe TV Cycles Delete Acoustic test Signed-Off

System Change Notices

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