# Presentation: 733131

## SOLAR TERRESTRIAL RELATIONS OBSERVATORYCONFIRMATION REVIEW 

- Haydee Maldonado – STEREO Project Manager
- March 27,  2002

## Agenda

- Introduction	H. Maldonado
- Mission Overview	H. Maldonado
- Science Overview/Objectives	J. Davila
- Programmatics	H. Maldonado
- Program Assessment	A. Harper
- IRT Report	W. Taylor
- IRT Project Responses	M. Delmont

## Introduction

## Timeline

| EVENT | 1997 |  |  |  | 1998 |  |  |  | 1999 |  |  |  | 2000 |  |  |  | 2001 |  |  |  | 2002 |  |  |  |
| --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- |
| Pre-Concept Study and Report to the Science Definition Team |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |
| Pre-Phase A Conceptual Design Report |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |
| AO Release |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |
| Instrument Selection |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |
| Systems Requirements Review |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |
| Phase A Reports |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |
| Independent Assessment |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |
| Initial Confirmation Review |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |
| Instrument Preliminary Design Review |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |
| Mission Design Review |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |
| Confirmation Readiness Review |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |  |

- May 1999

- March 1999

- November 1999

- May 2000

- December 1997

- August 2000

- June 2001

- January 2001

- September 2001

- December 2001

- March 2002

**Timeline**

## Action Items from the CRR

- Clarify Success Criteria in terms of CME’s.
- The Level 1 Science document has been updated to include mission duration in terms of both time and minimum number of expected CME’s.
- Provide more detail in the Descope Plan – prioritize instrument pieces.
- The Descope plan has been updated to include all instruments, prioritized in terms of science return.
- The Descope plan includes costs savings at both the CRR and CDR.

## Action Items from the CRR Cont.

- Review with Codes 300 and 500 the PRA results and reliability decisions.
- Code 302 has put together the Mission PRA by directly working with the instrumenters and combining with the APL  spacecraft inputs.
- The results of the PRA and reliability approach have been accepted by codes 300 and 500.
- Adopt standards for dimensional systems use to avoid misunderstanding.
- The project will generate a dimensional units policy that will be used for mechanical interfaces, environments and analysis.   This policy will be reflected in interface control drawings, system and subsystem specifications, and other control documents.
-  It will be addressed in peer reviews and gate reviews.

## STEREO Team

**STEREO Team**

**Project Management**
**GSFC**

**Mission Integrator, **
**Spacecraft Fabricator,**
**Mission Operator**
**JHU/APL**

**SECCHI**
**(Sun Earth Connection **
**Coronal & **
**Heliospheric Investigation)**
**NRL**
- Dr. Russ Howard

**SWAVES**
**(STEREO/Waves)**
**Observatoire de Paris**
**UMN**
- Dr. Jean-Louis Bougeret

**IMPACT**
**(In-Situ Measurements of **
**Particles & Coronal **
**Mass Ejection Transients)**
**UCB**
- Dr. Janet Luhmann

**PLASTIC**
**(Plasma & Suprathermal Ion **
**Composition Investigation)**
**UNH**
- Dr. Antoinette Galvin

**Notes:**
Project Management
Ms. Haydee Maldonado, Project Manager – Goddard Space Flight Center

STEREO Mission Integrator and Spacecraft Fabricator
Mr. Ted Mueller, Project Manager – The Johns Hopkins Applied Physics Laboratory

Sun Earth Connection Coronal and Heliospheric Investigation (SECCHI)
Dr. Russell Howard, Principal Investigator – Naval Research Laboratory

In-Situ Measurements of Particles and Coronal Mass Ejection Transients (IMPACT)
Dr. Janet Luhmann, Principal Investigator – University of California, Berkeley

Plasma  and Suprathermal Ion Composition Investigation on STEREO (PLASTIC)
Dr. Antoinette Galvin, Principal Investigator – University of New Hampshire

STEREO/Waves (SWAVES)
Dr. Jean-Louis Bougeret, Principal Investigator – Observatoire de Paris – Meudon

## Responsibility By Institution

_**GSFC**_
- Project Management
- Instrument Management
- Project Scientist
- Systems Engineering
- Mission Assurance
- Reliability
- Education and Public Outreach Coordinator
- Science/Data Analysis
- Data Archiving
- COR1, SEP, and MAG Instrument Developer
_**NRL**_
**SECCHI** Suite Development and Management
- Science/Data Analysis
_**UCB**_
**IMPACT** Suite Development and Management
- Science/Data Analysis

_**JHU/ APL**_
- Mission Integrator
- Mission Design
- Spacecraft Developer
- Systems Engineering
- Mission Integration and Testing
- Launch Vehicle Interface
- Mission Operations
- Ground Systems
_**UNH**_
**PLASTIC **Instrument Development and Management
- Science/Data Analysis
_**U of Minnesota/ Obs. of Paris**_
**SWAVES** Instrument Development and Management
- Science/Data Analysis

## Mission Overview

## Overview

- Total Cost:  $395.5M ( including 3 years of Data Analysis)
- Each Observatory
- Volume:  1.2 w x 2.0 l x 1.5 h  meters
- Mass:	      468 kg (dry mass)
- Power:     453 W (EOL)
- Launch Vehicle:  Delta 2925-10L
- Launch Date:  November 2005
- Data Policy:  Open data policy.  Data will be publicly available

## Stereo Mission

- Two Functionally Identical Spacecraft
- Heliocentric Orbits at 1 AU
- One Leading Earth
- One Lagging Earth
- 22°/yr Drift from Earth Orbit

**22****°/yr**

**22****°/yr**

**Lead**

**Lag**

**Earth Orbit**

**CMEs**

**CME**
**Propagation**

## STEREO Mission Design

**Lunar Orbit**

**22****°/yr Lead**

**22****°/yr Lag**

**S1**

**S2**

## STEREO Mission Success CriteriaJoseph M. DavilaNASA-GSFCGreenbelt, MD 20771Joseph.Davila@gsfc.nasa.gov

## Science Objectives

- Understand the causes and mechanisms of CME initiation
- Characterize the propagation of CMEs through the heliosphere
- Discover the mechanisms and sites of energetic particle acceleration in the low corona and the interplanetary medium
- Develop a 3D time-dependent model of the magnetic topology, temperature, density, and velocity structure of the ambient solar wind

## STEREO Instruments

**SECCHI** - Remote Sensing Package that will track Coronal Mass Ejections (CMEs) from the Sun to the Earth.
- Two White Light Coronagraphs (**COR1, COR2**) - *COR1 explores 1.4 – 4 Rsun. COR2 explores 2 – 15 Rsun*
- Extreme Ultraviolet Imager (**EUVI**) - *Looks at the upper chromosphere and innermost  corona*
- Heliospheric Imager (**HI1, HI2**) - *Observes Coronal Mass Ejections from the Sun to the Earth (12 – 300 Rsun)*
**IMPACT**- will sample the 3-D distribution of solar wind plasma electrons, the characteristics of the energetic particle ions and electrons, and the local magnetic field.
- Solar Wind Experiment (**SWEA**) - *Measures ~0.2-1 keV electrons with wide angle coverage*
- Suprathermal Electron Telescope (**STE**) - *Measures electrons from 5-100 keV with wide angle coverage*
- Magnetometer Experiment (**MAG**) - *Measures the vector magnetic fields in the range of +/-512 nT range with 0.1 nT accuracy*
- Solar Energetic Particle Experiment (**SEP**) Suite
*Measures electrons from 5-100 KeV, 30-400 KeV, 1-8 MeV*
*Measures protons from 30-2000 KeV/nuc, 13-40 MeV/nuc*
*Measures helium ions from 30-2000 KeV/nuc, 1.5-25 MeV/nuc, 13-40 MeV/nuc*
*Measures heavier ions form 30-2000 KeV/nuc, 30-80 MeV/nuc*
**PLASTIC** - will provide the plasma characteristics of electrons (1-1000 eV) protons, alpha particles, and heavy ion (300-8000 eV) that characterize the CME plasma.
**SWAVES** - in-situ as well as remote sensing instrument.  Tracks CME Driven Shocks from the Corona to the Earth.

## STEREO Observatory

**Deployed SWAVES **
**Electric Field Antenna**
**(3 places)**

**Deployed**
**IMPACT Boom**

**IMPACT**
**Solar Wind Electron Analyzer (SWEA)**

**IMPACT**
**Suprathermal Electron Detector**
**(STE)**

**IMPACT**
**Magnetometer**
**(MAG)**

**Deployed**
**High Gain RF**
** ****Antenna**
**(HGA****)**

**SECCHI **
**Heliospheric Imager**
**(HI)**

**SECCHI**
**Sun-Centered Imaging**
**Package (SCIP) Assy**
**(COR-1, COR-2, EUVI, GT)**

**Low Gain RF**
**Antenna (2)**
**(LGA)**

**Sun Sensor (5)**

**Adapter Ring**

**Bi-fold Solar Panel**

**Inertial Measurement Unit (IMU)**

**PLASTIC Instrument**

**IMPACT SEP**

**+X is Sun direction**

**STEREO Observatory**

## STEREO “Firsts”

- Two spacecraft for STEREO observation, optimum for 3D measurements
- Unique vantage point for observing Sun-Earth connection, optimum for development of predictive capability

## Level 1 Science Requirements

- _NOTES_
- The four science objectives are split into 17 Level 1 measurement requirements
- Some measurements (C, D, E) are defined for three heliospheric regions, low and upper corona, and interplanetary medium (IPM)

## Level 1 Science Requirements (2)

## Full Mission Success

**Full Mission Success**

- L1 requirement

- 12 different instrument combinations can satisfy these four L1 requirements

## Full Mission Success (2)

**Full Mission Success (2)**

## Full Mission Success (3)

**Full Mission Success (3)**

## Full Mission Success

- For Full Mission Success, the seventeen (17) measurement requirements shall be obtained over the prime mission life of two years using both STEREO spacecraft.  Assuming a CME rate consistent with the minimum of the solar magnetic activity cycle, STEREO expects to observe at least 60 CMEs in remote sensing instruments and at least 24 interplanetary events in-situ.

## Mission Phases

**Mission Phases**

## Coronagraph Imaging

- Solar disk is 106 times brighter than the corona
- The central part of the field is blocked to eliminate the bright disk
- The surrounding coronal structure is  brightest when within +/- 30 degrees of the plane of the sky as seen from the spacecraft

## Stereo Imaging with COR1 or COR2

- No overlap in line of sight (LOS) at intermediate separation angles
- Overlapping LOS exists at small angles, and large separation angles

## Full Mission Observational Capabilities

| Mission Phase |  | Remote Sensing | In-Situ |
| --- | --- | --- | --- |
| Prime Stereo Science |  | Stereo view of CMEs and their propagation for all instruments | Multipoint observation of Earth directed CMEs |
| Multipoint Science |  | Halo and limb CMEs and their propagation
HI and SWAVES stereo | Multipoint observation of Earth directed CMEs |
| Predictive Science |  | STEREO-A at quadrature with STEREO-B 
Stereo view of Earth directed CMEs | STEREO-A at quadrature with STEREO-B |

## Minimum Mission Success

**Minimum Mission Success**

- O’s req’d for 2 years

- X’s & O’s req’d for day 0-240

- L1 requirement

## Minimum Mission Success (2)

**Minimum Mission ****Success (2)**

## Minimum Mission Success (3)

**Minimum Mission ****Success (3)**

## Minimum Mission Success

- For Minimum Mission Success, the seventeen (17) measurement requirements shall be obtained using both STEREO spacecraft for at least 150 days after achieving heliocentric orbit AND using one STEREO spacecraft for the remainder of the two-year mission.  Assuming a CME rate consistent with the minimum of the solar magnetic activity cycle, we expect to observe at least 13 CMEs in remote sensing instruments and 5 interplanetary events in-situ during the 150 day period.    For the remainder of the two-year mission, at least 47 CMEs in remote sensing and 19 interplanetary events in-situ are expected.

- Measurement values not enclosed in brackets indicate the accuracy required when both STEREO spacecraft are required to be operational.  Values in square brackets indicate the accuracy of the measurements required to be achieved to meet Minimum Mission Success criteria during that part of the mission when only one spacecraft is required.

## 

Programmatics

**Programmatics**

## Status of Documentation

| DOCUMENT | STATUS |
| --- | --- |
| International Letters of Agreement | Completed |
| STEREO Level I Requirements | In Signature Cycle |
| Program Configuration Plan | Completed |
| Project Plan | Completed |
| Risk Management Plan | Completed |
| Data Management Plan | Draft |
| Reliability Plan | Completed |
| Debris Assessment Preliminary Report | Draft |
| Mission Assurance Plan | Completed |
| Mission Requirements Document | Completed |
| IT Security Plan | Draft |
| Export Control Plan | Completed |
| Environmental Impact Plan | In Review |
| Project Service Level Agreements | Completed |
| Education & Public Outreach Plan | Completed |
| SMO Review Agreement | Completed |
| SWAVES B Phase Grant | Completed |
| IMPACT, PLASTIC SECCHI Instrument BCDE Contracts | Completed |

## System Margins

| Resource | Allocation | Current Best Estimate | Margin4 |
| --- | --- | --- | --- |
| Dry Mass (kg)5 | 1138 | 937 | 18% |
| Orbital Avg power EOL (W)1 | 586 | 453 | 23% |
| Battery capacity SOC at sun-acq post launch2 |  |  | 48% |
| Science data storage (Gbit) | 8.1 | 6.2 | 23% |
| Delta V m/s 6 | 200 | 171 | 14% |
| RF links3 |  |  | 3dB |

| 1 | EOL power for behind spacecraft at aphelion after two years | 4 | Margin = (Launch capability – CBE)/Launch capability |
| --- | --- | --- | --- |
| 2 | Worst case launch scenario, 1 failed pressure vessel | 5 | Fuel and tank sized for full launch mass capability |
| 3 | At 2 year mark, data rate will be reduced if mission extended | 6 | 3 sigma dispersions & launch conditions, worst day of launch window |

## STEREO Top Level Requirements Flow

- Mission Assurance Requirements
- (460-RQMT-0005)

- Mission Requirements Document
- (460-RQMT-0001)

- System Requirements

- IMPACT
- Requirements

- SWAVES
- Requirements

- IMPACT ICD
- (7381-9012)

- SWAVES ICD
- (7381-9013)

- L-1 Science Requirements
- (Appendix A 460-Plan-0033)

- GEVS-SE

- Instrument Mission Assurance
- Requirements (460-RQMT-0022)

- Project Data Management Plan
- (460-Plan-0039)

- PLASTIC
-  Requirements

- PLASTIC ICD
- (7381-9014)

- SECCHI
-  Requirements

- SECCHI ICD
- (7381-9011)

- STEREO Science Center
- Functional Requirements

## Stereo Baseline Schedule

**STEREO PROJECT**

**ACTIVITY NAME**

**Major**** Milestones**

- 12/04

- 11/05

- 2/00

- 11/05

- 8/04

- 7/05

**TIMENOW:**

- 12/99

**2000 **

- Q1

- Q2

- Q3

-    Q4

**2001**

**2002**

**2003**

**2004**

**2005**

-    Q4

**‘****99   **

- 12/99

- 11/02

- Inst.CDR

- Deliver Instruments

- 8/04

- 11/04

- 11/05

- STEREO Dual S/C Launch

**Instrument Selection**

**Phase  A**

- Instrument Selection

**Bridge Phase**

**Phase B**

- 3/02

**Phase C/D**

**- Spacecraft Development**

- 11/05

**- Instrument Development**

- 11/04

**- Begin Instrument Del.**

- Begin Instrument Deliveries

**- Begin Instrument Int.**

- 8/04

- Begin Instrument Integration

**- Integration & Test**

- 12/03

**- Spacecraft Int.**

- 8/04

**- Instrument Int.**

**- Observatory Testing**

**- Launch Ops**

- 9/05

- 11/05

- 12/03

- 7/04

- 9/00

- 12/00

- FY

- 9/00

- 11/00

- STEREO BASELINE SCHEDULE CHART 2/8/02

**2006**

- 3/02

- Rev.

- Conf.

***S/C***

***R***

***Inst.***

- 19 months

- 7 months

- 4 months

- 8 months

- 2 mnths

***Testing***

- PDR

- Inst.

- 9/01

- 12/01

- PDR

- Obs.

- 3/02

- 3/02

- 3/02

- 12/02

- Mission

- 12/04

- 7/05

***R***

- 12/03

- (7/7-8/30)

***R***

***R***

***R***

- CDR

**Stereo Baseline Schedule**

## STEREO Contingency Summary Report

| INSTRUMENTS |  | REQUIRED DELIVERY DATE | PLANNED DELIVERY AS OF 1/31/02 | CONTINGENCY |
| --- | --- | --- | --- | --- |
| SECCHI | 1 | 10/12/04 | 7/12/04 | 63 Days |
|  | 2 | 11/08/04 | 8/12/04 | 60 Days |
| IMPACT (critical path) | 1 | 9/01/04 | 6/22/04 | 50 Days |
|  | 2 | 9/15/04 | 6/22/04 | 50 Days |
| PLASTIC | 1 | 9/27/04 | 7/8/04 | 57 Days |
|  | 2 | 9/30/04 | 7/8/04 | 60 Days |
| SWAVES | 1 | 8/16/04 | 1/16/04 | 150 Days |
|  | 2 | 8/25/04 | 1/16/04 | 157 Days |
| MISSION CONTINGENCY |  |  |  |  |
| SPACECRAFT
Pre Observatory I & T | A/B | 8/25/04 | 7/2/04 | 40 Days |
| Post Observatory I & T |  | 11/15/05 | 9/19/05 | 41 Days |
|  |  |  |  | 81 Days |

## Descope Plans

- Descope options are ranked in order of science priority as defined for STEREO by HQ Program Scientist and GSFC Project Scientist.
- No single instrument is required to meet the Level 1 science requirements.  At any time during the program, any instrument could be removed if needed.

## Stereo Descope Plan

**Stereo Descope Plan**

| Description | Mass
(kg) | Power
(W) | CR Cost
($M) | Cost Savings
CDR ($M) | Schedule | Risk | Science
Impact | Implement Date |
| --- | --- | --- | --- | --- | --- | --- | --- | --- |
| SECCHI Fine Pointing System | -- | -- | 0.5 | 0 | -- | -- | Degraded B, C1, D1, E1 | Confirmation Review (CR) |
| Remove SEP | 4.2 | 3.2 | 5 | 3.8 |  |  | F, G | Mass: CDR
Power: Anytime |
| Remove STE, SWEA, and simplify boom | 10 | 2.5 | 1.3 | 0.4 | -- |  | F, G, H, I, J | Mass: CDR
Power: Anytime |
| Remove SWAVES | 11.4 | 10.2 | 6 | 5 | -- |  | A, C3, D3, E3, F, G, H, I | Mass: CDR
Power: Anytime |
| Remove HI | 9.84 | 6 | -- | -- | --
 |  | C2,D2,E2,C3,D3,E3,J | Mass: CDR
Power: Anytime |
| Remove COR1 | 7.15 | 2.0 | 3 | 1.5 | -- | -- | A, B, C1, D1, E1 | Mass: CDR
Power: Anytime |
| Remove PLASTIC | 11.6 | 8.9 | 7.2 | 6.6 | --
 | --
 | H ,I, J | Mass: CDR
Power Anytime |
| Remove MAG | .6 | .4 | 1.08 | .75 | --
 | --
 | K | Mass: CDR
Power: Anytime |
| Remove EUVI | 6.41 | 3 | 2.5 | 1.0 | -- | --
 | A, B, C1, D1, E1 | Mass: CDR
Power: Anytime |
| Remove COR2 | 8.1 | 2 | 3 | 1.5 | --
 | --
 | B, C1, D1, E1, C2, D2, E2
 | Mass: CDR
Power: Anytime |
| Reduce Data Volume | -- | TBD | -- | -- |  |  | All | CDR |
| Reduced/Accelerated Testing | -- | -- | -- | -- |  |  | -- | If needed during I&T |
| Limited Selective Parallel I&T | -- | -- | -- | -- |  |  | -- | If needed during I&T |

## Cost Estimate Methodology Spacecraft Bus

- STEREO Grassroots was developed and compared to the TIMED implementation actual cost data
- STEREO mission unique complexity was added to compensate for the design and mission complexity differences
- Recommendations from RAO to add additional schedule, cost and reserves were implemented prior to Initial Confirmation Review
- JHU/APL Cost Estimation Approach
- Detailed bottoms up cost estimate generated at Concepts     	Development Stage and refined at PDR.
- High Degree of correlation between the Aerospace Small Satellite Cost Model 2000

## Cost Estimate Methodology Spacecraft (Continued)

- Non-Recurring Cost Savings
- MESSENGER is a sister mission to STEREO developed at APL
- MESSENGER/STEREO is leveraging the TIMED/CONTOUR design for the Power Distribution Unit and the Power System Electronics
- STEREO is sharing non-recurring costs of their new designs with MESSENGER
- STEREO will directly benefit of development effort carried by these two APL missions, scheduled for completion prior to STEREO.

## Spacecraft Design Commonality

**Spacecraft Design Commonality**

**Notes:**
C&DH: 		50% -60% reuse of design and 30% of code
G&C: 		30%  reuse of design and 10% of code
Earth Acq: 	60 % reuse of design and 25% of code
Boot:  		40 % reuse of design and 25% of code

## APL Phase C/D Cost History

- Phase C/D recent program cost history data percent growth from initial cost  estimate
-  		_**Program**_**	****	****	****        **_**Cost Growth**_
- NEAR				(-) 7%
- ACE				(-) 10%
- TIMED (without launch delay)		(+) 7%
- CONTOUR			0% (cost to completion estimate)
- APL’s proposal states that their historical performance is within ± 8% for phase C/D estimates generated at the end of Preliminary Design Review.

- (-) indicates returned funds
- (+) indicates cost growth beyond original cost estimate

## NOA Requirements

## Project Cost vs. Independent Cost Estimates

**	****	****         ****	****    ****	**** ****	****	****	****	****Project****	****	**** RAO****	****RAO ******** ****	****  ****	****IPAO ****	****	****IPAO ******** ****	****	****	****	****	****	****       ****	****   ****	****	****	****	****	****	****Difference****	****	****	****	****Difference**
- Mission  Management				$10.1			$12.2	+18%			$10		0%
**Spacecraft & Ground**				_**$107.5**_		_**$139.6**_	+30%**	****	****	****$**_**148**_		+38%
- 	Spacecraft Bus Hardware (2)	 	$63.7			$91.7				$89
- 	Spacecraft Bus I&T and MSI&T (2)		$31.9			$33.6		  		$491
- 	Ground System Development		$11.9			$14.3		 		$10
**Payload**						_**$62.3**_			_**$75.9**_	+22%**	****	****	**_**$54**_		-15%
- SECCHI Instrument Suites (2)			 $40.4			 $46.6				$35
- SWAVES Instruments (2)				 $  5.6			 $ 7.5				$5
- PLASTIC Instruments (2)				 $  5.1			 $  8.3				$4
- IMPACT Instrument Suites (2)			 $11.3			 $13.5				$10
- 		**Phase C/D  SUBTOTAL****	****	****	****$179.8****	****	****$227.7****	****+27%****	****	****$212****	****	****+18%**
- MO&DA						      $59.7		    $57.1		        	 	    $61
- LV & LV Services				                 $63.4	      		$63.4				    $63.4
- 	**Phase C/D/E SUBTOTAL         ****	****	****$302.9****	****	****$348.2****	****+15%****	****	****$336.4****	****	****+11%**
- Reserves						      $43.4		    $68.3	+57%  		    $502		+15%
**Phase C/D/E SUBTOTAL PLUS RESERVES       ****	****$346.3****	****         ****$416.5****	****+20%****	****	****$386.4****	****	****+11%**
- Formulation						  $49.1		  $39.6				  $50
**TOTAL COST TO NASA****	****        ****	****$395.5****	****	****$456.1****	****+15%****	****	****$437****	****	****+10%**
**With additional $11M****	****	****$406.5****	****	****	****	****+12%****	****	****	****	****+7.5%**

- 1includes Instrument to Bus I&T        2for 70Th percentile

**Project Cost vs. Independent Cost Estimates**

## Acquisition

- Spacecraft/Mission Integration
- JHU/APL Phase C/D/E task awaiting confirmation
- Instrument Contracts awaiting confirmation
- Launch Services
- KSC ready to initiate Boeing contract.
- DSMS/DSN
- Project Service Level Agreements (PSLA) are in place

## STEREO Risk Management

|  |  |  |  |  |
| --- | --- | --- | --- | --- |
|  | SC005 |  |  |  |
|  |  | SC003 |  | SC002 |
|  |  | IMP003 | IMP002 | SC004 |
|  | OB003 | OB004
PRO003 |  | SC001 |

- Risks as of 3/13/02

**1**
**Minimal**

**2**
**Minor**

**3**
**Medium**

**4**
**Major**

**5**
**Unacceptable**

**Very Low 1**

**Low  2**

**Medium 3**

**High 4**

**Very High 5**

**SC002** - Detumbling using thrusters in the blind
**IMP002** – Failure of IMPACT boom to fully deploy
**SC001** – Failure of Non-Redundant Component on the Spacecraft
**SC004** – Spacecraft Separation
**PRO003** – Instrument Single Point Failure
**SC005** – Spacecraft Software Schedule
**SC003** – No Closed Loop Test between GT and GNC
**OB004** – Contamination Control
**OB003** – Custom ASICS
**IMP003** – Boom fails to deploy

**IMPACT**

## Export Control Status

- Export/Import Control Plan completed
- All six LOA’s has been signed (France, Germany, Switzerland, ESA, Hungary, United Kingdom)
- Import Certification Complete
- Lockheed and Praxis have completed TAA
- APL and SWALES have initiated TAAs
- Universities have alternative paths

## IV&V

- IV&V West Virginia has completed their final Criticality Analysis and Risk Assessment (CARA) and provided an IV&V Project Plan to the STEREO Project
- IV&V activities for observatory flight software will focus on:
- Requirements traceability analysis
- Software Design Analysis
- Code Analysis
- V&V Test Program
- MOA for FY02 through FY05 is currently in the review cycle
- IV&V activities will commence immediately following MOA approval by the STEREO Project

## Technology ReadinessLevel-Spacecraft

| Spacecraft Subsystem | Technology Readiness
Level/  Heritage |
| --- | --- |
| Structure/Mechanical | 6 / ACE |
| Thermal Control | 7 / ACE  |
| Power Source, Storage and Distribution | 7 / ACE |
| Communications | 7 / NEAR |
| Command & Data Handling Subsystem | 6 / MESSENGER |
| Attitude Determination and Control | 7 / NEAR |
| Auxiliary Propulsion | 7 / ACE |

## Technology ReadinessLevel- Instrument

| Instrument | Technology Readiness Level/ Heritage |
| --- | --- |
| SECCHI |  |
|      HI | 5 / HELIOS, SOHO-LASCO C3 Coronagraph |
|      COR1 | 6 / MAUNA LOA Coronagraph (ground), SOHO – LASCO C1 Coronagraph |
|      COR2 | 6 / SOHO - LASCO C2 & C3 Coronagraphs |
|      EUVI | 7 / SOHO – EIT, TRACE |
| IMPACT |  |
|      SEP |  |
|      SEPT NS | 7 / ISEE, SOHO, ULYSSES, WIND |
|      SEPT E | 7 / ISEE, SOHO, ULYSSES, WIND |
|      LET | 7 / WIND, ACE, GEOTAIL |
|      HET | 7 / SAMPEX, IMP7&8, PIONEER |
|      SIT | 7 / WIND, ACE |
|     MAG | 8 / CLUSTER, WIND, MGS, ACE, LP |
|     SWEA | 7 / WIND, FAST, CLUSTER GIOTTO |
|     STE | 7 / WIND, HESSI |
| PLASTIC | 6 / CLUSTER-CODIF, ACE |
| SWAVES | 7 / WIND ISEE, ULYSSES, FAST, CASSINI |

## Heliosphere Imager (HI)

- HI Instrument Specification for Straylight Rejection
- HI-1: 10**-13** Normalized Brightness (Verified on previous program at NRL)
- HI-2: 10**-15** Normalized Brightness
- HI Test Schedule
- HI-1/2 Breadboard Straylight Rejection Test (in Air): Complete/successful
- HI-1/2 Breadboard Straylight Rejection Test (in Vacuum): May 2002
- HI-1/2  Straylight testing analysis completion June 2002
- Straylight Rejection Acceptance Testing on HI-1 / HI-2 FM: Summer 2003

## HI Mitigation Plan

**HI Mitigation Plan**

- If specified results are not obtained the following will occur:
- HI-1 will add D-shaped Aperture Stop
- Change the field of view by increasing the height of HI-1  forward baffle
- The above will not affect Level 1 requirements

## COR1 is now at TRL 6 as a result of completion of successful sub-system model tests:
Successful vibration test of occulter-field lens assembly (Aug 2001)
Thermal-vac tests (balance and cycles) of first two tube segments validated thermal model predictions (Nov 2001)
Breadboard optical performance tests demonstrated S/N requirements were achieved (Jun 2001)
Detailed schedule for COR1 ETU has been submitted
COR1 door, mechanisms, camera, and electronics are all part of common SECCHI components with flight heritage.

- Successful vibration test of occulter-field lens assembly (Aug 2001)
- Thermal-vac tests (balance and cycles) of first two tube segments validated thermal model predictions (Nov 2001)
- Breadboard optical performance tests demonstrated S/N requirements were achieved (Jun 2001)
- Detailed schedule for COR1 ETU has been submitted
- COR1 door, mechanisms, camera, and electronics are all part of common SECCHI components with flight heritage.

**COR1 Readiness**

## STEREO EPO Efforts

- STP Program provides overall coordination of outreach efforts
- Adheres to Office of Space Science E/PO Strategic Plan with emphasis on formal and informal education
- Organizational structure includes multi-tiered level of support to ensure quality and consistency of program and mission level efforts
- Promotes excellence in science, mathematics, engineering and technology education through direct involvement in partnerships, workshops and internships
- University Grants – University of Puerto Rico at Mayaguez
- School Partnerships – include schools from MA, MD, VA, D.C., PA, CT and Puerto Rico
- Summer Institutes – Creating an inclusion model for K-14 Space and Earth Science inquiry based instruction
- Project 2061- Workshops for in-service and pre-service teachers – mapping conceptual connections among the National Standards, Benchmarks and Learning outcomes in Space Science
- Student and Teacher Summer Internships
- Sponsoring NASA based competitions (robotics, engineering...)
- Partnerships with Radio Observatories, Planetariums and Museums
- Collaborates with the OSS Sun-Earth Connection Education Forum, GSFC Education Office and Education Resource Centers

## STEREO EPO Efforts

- Instrument Principle Investigators have conducted the following activities:
- Internships for Teachers – Secondary Education Teacher sponsored by NRL to develop Sun-centered planetarium Show using simulations of STEREO operations and observations
- Teacher Development Workshops – Sponsored by UNH for professional development of high school educators in the science of Electromagnetism and the Light Spectrum
- Public Speaking Engagements and Classroom Visits – Conducted by numerous STEREO scientists and included Career Day, Oregon Star Party/Rose City Astronomers, activities to enhance the Space Weather Exhibit, lecture series for scientific associations, and space science and astrophysics lectures at the Christa McAuliffe Planetarium
- Student Internships – Students sponsored by UNH engaged in software development, mechanical design and lab simulation testing
- Solar Eclipse Event 2001 – Scientists and EPO professionals extensively supported the live web-cast event involving over 50 national and international planetariums, museums and community facilities

## Recommendation from the GSFC PMC

- STEREO is ready to proceed into implementation
- GSFC’s Resource Analysis Office estimate assesses the spacecraft bus as under funded.
- APL has good cost history, but potential still exists for cost growth; however, APL deserves to have the opportunity to meet their cost commitment.
- Thus, while we believe that an additional $11M should be  added as contingency against potential cost growth, it should be held at the Program level, not the project level.
- Use of this contingency would require special HQ level review, and will be placed back into the STP program if STEREO meets its cost goals.

## Summary

- The STEREO Project considers adequate resources are in place to proceed to the  implementation phase.

## Program Assessment

## Program Contingency Plans

- STP, as a line of missions, can manage contingency at program level
- As liened contingency
- As schedule in follow on missions (á la Explorers)
- Program agrees with recommendation to hold $11M in contingency for STEREO
- STEREO will manage to $395.5 budget and implement descopes and other management tools as required to contain growth.
- STEREO cost and schedule will be reviewed at the program level in the CDR timeframe to assess progress

## Contingency Continued

- STEREO will be assessed again at final available decision point in mid FY04
- Prior to procurement of MMS spacecraft
- 		OR
- Start of GEC formulation, instruments selected and on phase A contracts
- STEREO resource assessment can be made with high fidelity for the March 04 decision date
- Individual SECCHI instruments schedule to be complete or near completion
- COR 1 and 2  March 04
- HI 		     May 04
- EUVI	     Jan 04
- Electronics       Jan 04
- Delivery on significant portion of IMPACT instruments
- Booms, SWEA, STE, MAG by March 04

## Contingency Summary

- Program can lien contingency at program level
- Contingency can be held as schedule to follow-on missions until decision point in mid FY04
- Code S Assessment will be made prior to decision point for:
- Go ahead to follow on missions (MMS, GEC, MC) on original schedules
- 					OR
- Addition of $ to STEREO, with subsequent schedule slips to one of more follow-on missions.  Early assessment shows that GEC can best absorb schedule hits

## Acronyms

- ASRG	Astrophysics and Space Research Group
- CCD	Charge Coupled Device
- CCR	Configuration Change Request
- CDR	Critical Design Review
- CEB	Camera Electronics Box
- CM	Configuration Management
- CME	Coronal Mass Ejections
- COR	Coronagraphs
- DLR	Deutsches Zentrum für Luft and RaumfahrtDPM	Deputy Project Manager
- DSMS	Deep Space Mission Services
- EOL	End of Life
- EPA	Environmental Protection Agency
- EPO	Education and Public Outreach
- ER	Established Reliability
- EUV	Extreme Ultra Violet Imager
- FOR	Flight Operations Review
- FPA	Focal Plan ArrayFRR	Flight Readiness Review
- GSFC	Goddard Space Flight Center
- GSRR	Ground Systems Requirement Review
- GT	Guide Telescope
- HGA	High Gain RF Antenna
- HI	Heliospheric Imager
- IA	Independent Assessment
- IAS	Institut d’Astrophysique Spatiale ICD	Interface Control Document
- IM	Instrument Manager
- IMPACT	In-situ Measurement of Particles and Coronal Mass Ejection Transients

## Acronyms Continued

- IMU	Inertial Measurement Unit
- IOTA	Institut d’Optique Theoretique et AppliqueeIPM	Interplanetary Medium
- JHU/APL	Johns Hopkins University/Applied Physics Laboratory
- LGA	Low Gain RF Antenna
- LMSAL	Lockheed Martin Solar and Astrophysics LabLOA	Letter of AgreementLOS	Line of Sight
- LRR	Launch Readiness Review
- M&P	Materials and Process
- MAG	Magnetometer Experiment
- MCR	Mission Confirmation Review
- MEB	Mechanisms Electronics Box
- MOC	Mission Operations Center
- MOR	Mission Operations Review
- MRR	Mission Readiness Review
- MSPSP	Missile Systems Pre-launch Safety Package
- NCR	Non-Conformance Report
- NDIPR	NASA Defense Procurement Request
- NPSL	NASA Part Selection List
- NRAs	NASA Research Announcements
- NRL	Naval Research Laboratory
- NSPARS	Non-Standard Parts Approval Request
- ORR	Operational Readiness Review
- OSS	Office of Space Science
- PDR	Preliminary Design Review
- PEB	Parts Control Board
- PER	Pre-Environmental Review
- PFR	Problem Failure Report
- PI	Principle Investigator
- PLASTIC	Plasma and Suprathermal Ion and Composition
- PM	Project Manager

## Acronyms Continued

- POP	Program Operating Plan
- PPARC	Particle Physics CNESPRA	Probabilistic Risk Assessment
- PSR	Pre-Ship Review
- PSLA	Project Service Level Agreements
- RAL	Rutherford Appleton Labs
- SCIP	Sun Centered Imaging Package
- SE	System Engineer
- SEB	SECCHI Electronics Box
- SEC	Sun-Earth Connection
- SECCHI	Sun-Earth Connection Coronal and Heliospheric Investigation
- SEE	Single Event Effects
- SEP	Solar Energetic Particle Experiment
- SMO	Systems Management Office
- SOC	State of Charge
- SR&QA	Safety Reliability and Quality AssuranceSRO	Systems Review Office
- STE	Suprathermal Electron Detector
- STEREO	Solar Terrestrial Relations Observatory
- STP	Solar Terrestrial Probes
- S/W	SoftwareSWAVES	STEREO Waves
- SWEA	Solar Wind Electron Analyzer
- UCB	University of California, Berkeley
- UK	United KingdomUMN	University of Minnesota
- UNH	University of New Hampshire
- WBS	Work Breakdown Structure

## Backup Charts

## Orbital Debris Assessment

- Projects are required to perform an orbital debris analysis in accordance with NMI 1700.8.
- The STEREO analysis will be based on the MAP report. Both missions use a Delta 7x25 with a STAR48 third stage and use the moon for a gravity assist maneuver. So debris generated and trajectories will be very similar.
- Final report will be completed prior to CDR.
- Preliminary report is in process
- Preliminary analysis shows no problems – no radiation source and no debris will be released during normal or contingency ops.

## IT Security

- IT Security paragraph has been applied to STEREO contracts
- Security requirements were reviewed with instrumenters, mission integrator, and GSFC IT security personnel
- Proposals have been received.  Costs are within budget allocations

## Work BreakdownStructure (WBS)

**Work Breakdown****Structure (WBS)**

**Notes:**
WBS defined to 3 levels
-Mission
-Major Element
-Subsystem
Spacecraft WBS extended to include sub-system level
Unique WBS among instruments accommodates complexity

## DELTA II 2925–10L Launch Vehicle

- 3rd Stage
- STAR 48B

**Two Piece Composite**
**Fairing**

**3****rd**** Stage Section**

**Stacked **
**Observatories**
**(Clocked 180****°)**
**Held Together by**
**V-band Clamp**

**Payload Section Dynamic Envelope:**
** ****108 in Diameter**
** ****10 ft Length**

## Data Flow/SSC Block Diagram

**MOC (APL)**

**Level-0 Data**
**Mission Data**
**(30 day archive)**

- Network Admin
- System Admin
- Programming
- Graphic Arts

**(socket, ftp get, ftp put, email, streaming, etc.)**

**SDAC (GSFC)**

**MOC-POC-SSC**
**Telemetry Interface**

**STEREO Science Center **

**Space Science Center (UCLA)**

- SWx, Level-0, and Mission Support Data

**Data Flow/SSC Block Diagram**

**SEC Missions**

## Data Policy	 

- STEREO data will be treated as public resource and will be delivered to public as soon as practical
- During three months check out and calibration STEREO database available to international community through NASA data center
- After this period, the data will be made public with no more than a two-month delay.

## STEREO Behind Observatory

**Deployed SWAVES **
**Electric Field Antenna**
**(3 places)**

**Deployed**
**IMPACT Boom**

**IMPACT**
**Solar Wind Electron Analyzer (SWEA)**

**IMPACT**
**Suprathermal Electron Detector**
**(STE)**

**IMPACT**
**Magnetometer**
**(MAG)**

**Deployed**
**High Gain RF**
** ****Antenna**
**(HGA****)**

**SECCHI **
**Heliospheric Imager**
**(HI)**

**SECCHI**
**Sun-Centered Imaging**
**Package (SCIP) Assy**
**(COR-1, COR-2, UVI, GT)**

**Low Gain RF**
**Antenna (2)**
**(LGA)**

**Sun Sensor (5)**

**Adapter Ring**

**Bi-fold Solar Panel**

**Inertial Measurement Unit (IMU)**

**PLASTIC Instrument**

**IMPACT SEP**

**+X is Sun direction**

**STEREO Behind Observatory**

## Reserves Allocation

| Element Description | Phase C/D Cost | Grassroot Reserve Allocation %      wrt Total Cost | Estimate 
Reserve
 ($Million) | Percentage | Estimate Reserve Allocation Totals ($Million) |
| --- | --- | --- | --- | --- | --- |
| GSFC Project Management | 10.1 | 20% | 2.0 |  | 2 |
| OBSERVATORY (JHU/APL) | 98.1 |  |  | 20% | 19 |
| Project Management (JHU/APL) | 7.98 | 10% | 0.8 |  |  |
| Spacecraft (JHU/APL) |  |  |  |  |  |
| Structure | 3.02 | 25% | 0.8 |  |  |
| Thermal | 1.10 | 20% | 0.2 |  |  |
| Power Source Storage and Distribution | 18.05 | 20% | 3.6 |  |  |
| Communications | 12.08 | 25% | 3.0 |  |  |
| Command and Data Handling  | 16.06 | 15% | 2.4 |  |  |
| Attitude Determination and Control | 12.36 | 20% | 2.5 |  |  |
| Reaction Control/Auxiliary Propulsion | 0.60 | 15% | 0.1 |  |  |
| Observatory Integration & Test (JHU/APL) | 12.83 | 35% | 4.5 |  |  |
| Mission Operations Center (JHU/APL) | 8.64 | 15% | 1.3 |  |  |
| INSTRUMENTS | 62.3 |  |  |  | 17 |
| IMPACT (SUITE) | 11.3 |  |  | 29.0% |  |
|      IMPACT (UCB)          Project Management | 1.1 | 15% | 0.2 |  |  |
|      IMPACT (UCB)          Hardware and Manpower | 7.3 | 30% | 2.2 |  |  |
|      IMPACT (UCB)          Integration and Test | 2.3 | 35% | 0.8 |  |  |
|      IMPACT (UCB)          Payload Operations Center | 0.6 | 20% | 0.1 |  |  |
| PLASTIC | 5.0 |  |  | 21.0% |  |
|      PLASTIC (UNH)          Project Management | 0.5 | 10% | 0.1 |  |  |
|      PLASTIC (UNH)          Hardware and Manpower | 3.0 | 20% | 0.6 |  |  |
|      PLASTIC (UNH)          Integration and Test  | 1.3 | 30% | 0.4 |  |  |
|      PLASTIC (UNH)          Payload Operations Center | 0.3 | 10% | 0.0 |  |  |
| SECCHI | 40.4 |  |  | 28.8%
 |  |
|      SECCHI (NRL)           Project Management | 4.0 | 15% | 0.6 |  |  |
|      SECCHI (NRL)           Hardware and Manpower | 26.3 | 30% | 7.9 |  |  |
|      SECCHI (NRL)           Integration and Test  | 8.1 | 35% | 2.8 |  |  |
|      SECCHI (NRL)           Payload Operations Center | 2.0 | 15% | 0.3 |  |  |
| SWAVES | 5.6 |  |  | 20.0%
 |  |
|      SWAVES (UMN)       Project Management | 0.6 | 5% | 0.0 |  |  |
|      SWAVES (UMN)       Hardware and Manpower | 3.6 | 20% | 0.7 |  |  |
|      SWAVES (UMN)       Integration and Test | 1.1 | 30% | 0.3 |  |  |
|      SWAVES (UMN)       Payload Operations Center | 0.3 | 10% | 0.0 |  |  |

## Reserve Status

**$38.8M Unliened Reserves**

**$9.4M Liened Reserves**

**Reserve Status**

## Spacecraft Requirements Flowdown

**Spacecraft Requirements Flowdown**

## Risk Classification Description

**Risk Classification Description**

## STEREO Top Ten List

| Risk Identifier  |  | Description  | Initial Exposure | Risk Mitigation |
| --- | --- | --- | --- | --- |
| 1 | SC002 | Detumbling using thrusters in the blind. The current L&EO plan has both spacecraft detumbling using thrusters, autonomously, in the blind and simultaneously. This activity is potentially catastrophic if there is a phasing error (for example). | 15 | Baseline L&EO plan must be complete by CDR. APL conducting trade with the following options.
Add tracking assets to early timeline.
Shift timeline to gain earlier contract with existing assets.
Change deployment/detumble timeline to accommodate ground station viewing.
Reference Mission PDR RFA #18.
Trigger: 4/2002 in response to a PDR RFA. |
| 2 | PRO001 | Component or Instrument exceeds allocated Resources. Components or instruments that exceed their allocation will reduce the overall observatory margin. | 12 | Instruments and spacecraft are given their own allocations to manage.
Resource tracked and managed by project & mission integrator.
A formal mass & power tracking system has been established and is under CM.
Project holds non-allocated mass and power reserves.
Trigger: CDR 11/2002 |
| 3 | SC004 | Spacecraft Separation. The electronics that drive the separation system are single string. | 10 | APL is conducting a trade study to consider a fully redundant third stage separation detection and A/B separation system. Reference Mission PDR RFA #19.
Trigger: April 2002 |

## STEREO Top Ten List (Continues)

| Risk Identifier  |  | Description  | Initial Exposure | Risk Mitigation |
| --- | --- | --- | --- | --- |
| 4 | SC003 | No Closed Loop Test between the Guide Telescope and GNC planned. There is a possibility that pointing and jitter requirements may not be met. | 9 | NRL-provided GT model integrated to G&C test suite and Simulink models.
End-to-end testing will occur closed loop in a similar fashion to IMU and ST.
GT model to undergo IV&V.
Compreshensive testing for both GT and G&C to occur separately.
GT description and interface documented in ICD with spacecraft.
Phasing tests with flight GT to occur on both Observatories.
Trigger: Re-evaluate at CDR. |
| 5 | SC005 | Spacecraft Software Schedule. Flight Software is not at PDR level. It appears to be at the requirements and conceptual design level. | 8 | STEREO Project personnel will attend all flight software peer reviews leading up to the 4 CSCI software PDR’s (scheduled to occur in the May/June 2002 timeframe). Software milestones and schedule slips will be closely monitored by the STEREO SAM, and DCMA support has been initiated to provide software development surveillance at the JHU/APL facility. In addition, NASA IV&V support will be analyzing the flight software requirements and software design throughout the development lifecycle. Reference Mission PDR RFA #37.
Trigger: June 2002 |

## STEREO Top Ten List (Continues)

| Risk Identifier  |  | Description  | Initial Exposure | Risk Mitigation |
| --- | --- | --- | --- | --- |
| 6 | IMP002 | Failure of IMPACT boom to fully deploy. The spacecraft guidance and control system may be unable to control the observatory during propulsion maneuvers or may be unable to meet the jitter specification. | 8 | Complete Worst Case Analysis of partially deployed boom.
Use FTA to determine root causes and aid in contingency planning.
Test of prototype and flight boom.
Integrate FEM into observatory model.
Consider not deploying boom until observatory is in heliocentric orbit.
Trigger: Worst Case Analysis due 5/2002 |
| 7 | IMP003 | Boom fails to deploy. Unlike the boom fails to fully deploy risk, if the boom does not deploy at all there will be a loss of science. | 6 | Complete Worst Case Analysis of partially deployed boom.
Use FTA to determine root causes and aid in contingency planning.
Testing of prototype and flight boom.
Integrate FEM into observatory model.
There will be a loss of SWEA, MAG and STE science.
Trigger: Worst Case Analysis due 5/2002 |

## STEREO Top Ten List (Continues)

| Risk Identifier  |  | Description  | Initial Exposure | Risk Mitigation |
| --- | --- | --- | --- | --- |
| 8 | SC001 | Failure of Non-Redundant Component on the Spacecraft. The spacecraft has selected redundancy; impact of failure of non-redundant component could range from improper spacecraft operation up to not meeting minimum mission success criteria. As a result of mission level reliability analysis it may be necessary to add redundancy or otherwise increase reliability of single string items which would increase costs. | 5 | Use of grade 2 parts or better.
Comprehensive PRA to set priorities in determining areas where additional redundancy is warranted.
Use of FTA to determine root causes and aid in contingency planning.
Increased oversight of component development.
Environmental testing and qualification.
High reliability workmanship standards.
FMEA determines consequences of non-redundant component failures.
Trigger: Continuous review of FMEA and FTA; final at CDR |
| 9 | PRO003 | Instrument Single Point Failure. As a result of FMEAs and FTA it may be necessary to add redundancy or otherwise increase reliability of single string items which would increase costs. | 3 | Use of grade 2 parts or better.
Comprehensive PRA to set priorities in determining areas where additional redundancy is warranted.
Use of FTA to determine root causes and aid in contingency planning.
Increased oversight of component development.
Environmental testing and qualification.
High reliability workmanship standards.
FMEA determines consequences of non-redundant component failures
Trigger: Continuous review of FMEA and FTA; final at CDR |

## STEREO Top Ten List (Continues)

| Risk Identifier  |  | Description  | Initial Exposure | Risk Mitigation |
| --- | --- | --- | --- | --- |
| 10 | OB004 | Contamination Control. The STEREO instruments are sensitive to contamination by dust or particles and by hydrocarbon vapors and liquids. | 3 | Contamination Committee has been formed. Includes representatives from each instrument, spacecraft, and project office.
Contamination Control Plan addresses requirements and methodology to control contamination on the ground. Handling and cleaning procedures have been presented to instrument teams and spacecraft during phase A.
Project has hired a dedicated contamination engineer to assist the instrument teams.
Contamination requirements are a subject during design reviews at vendors, subsystems reviews and observatory level reviews.
Materials are evaluated and controlled.
Trigger: CDR 11/2002 – A contamination control plan should be in place
Trigger: 10/2004 Instrument Delivery |
| 11 | OB003 | Custom ASICs. There are several custom ASICs planned to be used in the STEREO design. Bugs or schedule slips in the manufacture of the ASICs could adversely affect the schedule. | 2 | Instrument schedules were revised to plan for a second ASIC run as a contingency.
Trigger: CDR 11/2002 – ETU testing will demonstrate acceptability of ASICs. |

## Design Review Status

- All RFA’s from Instrument and Mission PDR have been negotiated and accepted by the project.
- All RFA’s have been assigned to individuals with expected due dates.
- Closure plan has been coordinated with SRO.

## RFA Status

|  | Total | Submitted | Closed | Draft Response | Need Response |
| --- | --- | --- | --- | --- | --- |
| IMPACT PDR | 29 | 21 | 18 | 8 | 0 |
| SWAVES PDR | 8 | 5 | 5 | 2 | 1 |
| SECCHI PDR | 42 | 22 | 18 | 19 | 1 |
| PLASTIC PDR | 17 | 9 | 7 | 0 | 8 |
| Mission PDR | 62 | 15 | 3 | 7 | 40 |

## Evaluation of MDR RFA’s

- Several recommendations on adding redundancy (eg. Processors, A/B separation devices, thermostats, IEM power supplies.)
- Each of these recommendations are being evaluated and trades are being performed. Expected resolution is 2 to 4 weeks.
-  Flight Software Readiness.
- Draft response submitted to the Project. Dates for design reviews and peer reviews established. S/W QA and IV&V being negotiated; draft plan exists.
- Environmental Verification of Hardware. There were several comments, suggestions.
- Detailed plans and Environmental Test Matrix are due as part of phase C effort.
- Peer reviews for all mechanisms

## Evaluation of MDR RFA’s

- Operational Design Robustness:
- Recommendations were made regarding autonomous thruster firing, safing mode, deployment within ground contact, and ensuring capability for single thruster firing. Increased staffing for early checkout and operations and providing backup commanding at the MOC were recommended.
- Each of these recommendations are being evaluated and trades are being performed. Expected resolution is 2 to 4 weeks.
- A response to the staffing is due in April.
- A response to providing backup commanding at the MOC is due this summer.

## Reporting

- Focused weekly meetings and telecons
- Project office receives from APL, UCB, UMN, UNH, and NRL:
- Monthly Reports
- Top Ten Risks
- Status Schedule
- Financial Reports
- Project generates analysis
- Technical accomplishments
- Technical challenges and issues
- Schedule Status
- Gantt and pert network review
- Milestone tracking
- Cost Status
- Cumulative cost actual vs. Plan
- 533 analysis summary
- Affirmation that cost at projected completion remains within budget allocation
- Identification of any cost phasing issues
- Project Top Ten Risks

**Notes:**
Under Monthly Reports, Instrument Teams also produce mass and power updates.

## Reporting (Continued)

- Monthly assessment presented to STP Program Office and Goddard PMC:
- Project Manager Assessment
- Summary fever chart of major elements and subsystems (current and 2 past months)
- Significant progress
- Problems/issues
- Programmatic impact
- Action plan with completion dates
- Current status of resolution
- Technical resource status (mass, power)
- Schedule status
- Master Gantt
- Significant milestones (current month +8, -3)
- Major milestone total slack summary
- Contingency
- Cost
- Actuals/Plan
- Reserve Status

## Cost/ Schedule/ Technical Reporting 

|  | Week 1 | Week 2 | Week 3 | Week 4 |
| --- | --- | --- | --- | --- |
| Received Reports |  |  |  |  |
| Mass/ Power  |  | x |  |  |
| Schedules |  | x |  |  |
| Financial Reports |  | x |  |  |
| Final Report ( Top 10 Risks, Technical Progress, Issues) |  |  |  | x |
| Reviews  |  |  |  |  |
| Subsystem Level |  |  |  |  |
| Schedule meetings |  |  | x |  |
| Financial review |  |  | x |  |
| Project Level |  |  |  |  |
| Technical and management review |  |  |  | x |
| Risk Management- Top 10 Risks  | x |  |  |  |
| Meetings |  |  |  |  |
| Subsystem Level |  |  |  |  |
| Instrument Systems | x | x | x | x |
| SWAVES Telecon | x | x | x | x |
| IMPACT Telecon | x | x | x | x |
| PLASTIC Telecon | x | x | x | x |
| SECCHI Team  meeting | x | x | x | x |
| APL weekly ( Observatory Manager) | x | x | x | x |
| Project Level |  |  |  |  |
| Project Staff meeting | x | x | x | x |
| Team Telecon ( GSFC, APL, PI Institutions) | x | x | x | x |
| APL Coordination meeting |  | x |  | x |

**Cost/ Schedule/ Technical Reporting **

## APL Monthly Cost Variance Report

## EXAMPLE

**For WBS 200 PAYLOAD**

_**Cum Act**_

_**Actual**_

_**Plan**_

**15 M**

**14 M**

**13 M**

**12 M**

**11 M**

**10 M**

**9 M**

**8 M**

**7 M**

**6 M**

**5 M**

**4 M**

**3 M**

**2 M**

**1 M**

**0**

_**Mar 02**_

_**Apr 02**_

_**May 02**_

_**Jun 02**_

_**Jul 02**_

_**Aug 02**_

**1.5**

**1.5**

**1.5**

**2.5**

**3.5**

**5.0**

**Begin Proc of**
**Long Lead Items **

_**Schedule Integration**_
**Two Key Schedule Milestones will be selected **
**per Month & pulled, tracked, & statused from the **
**STEREO Subsystem Networks**
**Schedule Milestones are Determined by the following:**
**Impact to Cost – A schedule Driver**
**Project Life Cycle**
**Measurable**
**Milestones selected by Observatory/Instrument Manager**
**Reviewed on Mthly basis at  Stereo Technical**
**& Business Meetings**

**3/6**

**Begin Payload**
**Chamber Refrub **

**3/22**

**Plan -**

**Actual -**

**EXAMPLE**

## STEREO MASTER SCHEDULE

**STEREO**** ****MASTER SCHEDULE**

- J

- F

- M

- A

- M

- J

- J

- A

- S

- O

- N

- D

**2005**

- J

- F

- M

- A

- M

- J

- J

- A

- S

- O

- N

- D

**2004**

- J

- F

- M

- A

- M

- J

- J

- A

- S

- O

- N

- D

**2003**

- J

- F

- M

- A

- M

- J

- J

- A

- S

- O

- N

- D

**2002**

- J

- F

- M

- A

- M

- J

- J

- A

- S

- O

- N

- D

**2001**

**MISSION MILESTONES**

**PROJECT:**

**SPACECRAFT SUBSYSTEMS**

- MECH / STRUCTURAL / THERMAL

- GUIDANCE & CONTROL / FLIGHT S/W

- D

- N

**2000**

- RF COMMUNICATIONS / IEM / RIU

- POWER / PROPULSION

**INSTRUMENTS**

**SWAVES**

**SECCHI**

- COR-1 / COR-2

- EUVI / GT / HI-1 / HI-2 / Mechanisms

**IMPACT**

- Magnetometer / Boom / STE / SWEA

- LET / HET / SEPT / SIT

- IMPACT I & T

**PLASTIC**

- GROUND SYSTEM

- SCIP / SEB / CEB / FPA

**STEREO**

**KEY**

**- Start Milestone**

**- Finish Milestone**

**- Contingency**

**- SWAVES**

**- IMPACT**

**- PLASTIC**

**- SECCHI**

**- Critical Path**

- SPACECRAFT INTEG/TEST

**OBSERVATORY**

** **

**I & T**

**ENVIRONMENTAL TESTING**

**LAUNCH OPERATIONS / LAUNCH**

**CONTINGENCY SUMMARY**

- 8/11

- Begin Observatory Performance Tests

- Launch Site

- OBS A / B T/V Balance

- Begin Observatory I & T

- 6/29-8/24

- 12/23

- 6/28

- Begin S/C  I & T

- A

- B

- 3/16

- C&DH S/W BLD 3 / G&C S/W BLD 2

- Integrate A/B Power Elect

- 1/9

- 4/8

- A/B Propulsion Phasing Test

- Status As Of: 11/15/01

- 1/26-3/12

- 10/1-28

- 11/14-12/12

- 6/20-7/18

- 20 Days

- 20 Days

- 20 Days

- 35 Days

- 40 Days

**PROJECT PHASES**

- Instrument

- CoDR

- PDR

- Mission

- PDR’s

- Conf

- CDR’s

- Instrument

- CDR

- MOR

- PER

- FOR

- PSR

- FRR

- SRR

- GS

- 1

- 8/16

- 2

- 8/25

**PLASTIC**

- 1

- 9/27

- 2

- 9/30

**IMPACT**

- 1

- 9/1

- 2

- 9/15

- 1

- 10/12

- 2

- 11/8

**LRR**

- BP

- Phase B

- Phase C/D

**SWAVES**

**SECCHI**

- 2/12

- S/W Build 1

- 10/10

- S/W Build 2

- 10/20

- S/W Build 3

- 5/25

- S/W Build 4

- Del H/W Simulator

- 12/2

- Simulator Test & Eval

- 1/29

- GS SRR

- 11/01

- F

- 3/30

- D

- MOC to APL GSE ICD

- Complete Vib / Alive, A/B Functionals

- 11/28

- 7/3

- G&C GSE S/W BLD 2

- G&C FL S/W BLD 2

- G&C EA S/W BLD 2

- 3/15

- 3/17

- Final G&C Test Plan/Procedures

- Flexible Body Modeling

- 3/2

- Final NASTRAN
- Model from SEM

- 11/12

- Sys Engineering

- 2/16-3/12

- 11/29

- S/W Dev& Mgmt Plan

- S/W Build 5

- 11/14

- FL S/W Testbed BLD 1

- FL S/W Testbed BLD 2

- 6/12

- 5/24

- 5/13

- 12/8

- 11/4

- 9/2

- Jitter Analysis

- OBS Mass Properties

- 2/13

- 10/15

- 8/27

- Detailed S/C
- Thermal Analysis

- Prel Ther Dsgn

- 9/3

- Begin Solar Array Deployment Dsgn

- 12/12

- 2ndry Structure Dsgn Complete

- 9/2

-    Solar Array
- Contract Award

- SA Vendor CDR

- 11/14 - 12/12

- 12/15

- Solar Array to Mechanical

- 7/21

- PSE/PDU Del to I & T

- Begin Solar Array Spec Development

- N2 Heater

- 6/26

- 3/2

- Propulsion Vendor Selected

- 5/15

- 7/1

- Propulsion Contract Award

- 12/12 - Prop Sys Shipped to APL

- 1/21

- SA Vendor PDR

- 9/24- Propul Vendor PDR

- 8/29

- Ship S/C Structure to Vendor

- 4/2

- 10/6

- Begin TWTA
-   Spec Dev

- TWTA to S/C A/B

- A

- B

- 11/11

- All RFComp Proc Complete

- DSN Tests Complete

- 11/25

- GSE

- Dsgn

- 12/02

- 1/8

- Begin All RF Comm Comp Proc

- 12/3

- IEM Contract Award

- IEM I/F Card BB
-   Del to C&DH

- 6/28

- 10/1

- 11/3-SWEA FM1 to UCB

- 3/20

- Begin MAG ETU Dev

- 11/1

- MAG FPGA DSGN

- 4/17

- 12/1

- FM2 MAG to UCB

- MAG ETU to UCB

- 3/1

- SWEA ETU

- 5/1

- MAG ETU

- 6/2

- FM1 MAG

- FM2 MAG

- 11/18-FM1/2 Boom Avail

- 7/12

- Qual Boom

- 11/29

- Begin Boom
-     Flt Build

- 5/22

- Flt Boom Assy

- IMPACT FM1
-    EMC Test

- 11/19-20

- CDR

- 6/3

- FM1 PWR Supplies

- 12/3

- FM2 PWR Supplies

- 1/30

- STE FM2

- STE FM1

- STE ETU

- 9/30

- STE PDR

- FM1/2 SEP to UCB

- 9/11

- PDR

- 10/23

- FM1 IDPU Vib

- 12/23

- Assy IDPU FM1 LVPS

- 3/18

- FM2 IDPU

- IDPU S/W Bld # 3

- 3/4

- 8/23

- ETU IDPU

- 6/25

- 8/23

- ETU IDPU

- 3/01

- EM Entrance Dsgn

- EM Entrance Delivery

- 4/15

- FM Entrance Delivery

- 3/17

- 11/21-22

- CDR

- 4/28

- Flt ESA1 Del from Bern

- 6/28

-     UNH GSE Simulator Testing

- 3/28

- VLSI Testing

- Mechanical Dsgn

- 10/8

- Motherboard

- 5/2

- 6/3

- Flt LVC1 from UCB

- 12/3

- Flt LVC2 from UCB

- Converter Dsgn

- 1/8

- 7/8

- 4/18

- Flt Converter

- Flt S/W Final Bld

- 12/2

- Flt Integ @ Minnesota

- Flt DPU

- 1/9

- Envir @ GSFC

- GSE H/W

- 5/11

- 5/16

- GSE S/W Final Bld

- 3/7

- DPU Flt S/W

- 1/30

- Pack & Ship to APL

- 1/31 - 8/24

- 7 Months Contingency

- SPACECRAFT

- INSTRUMENTS

- 1/31 - 8/24

- SWAVES

- 7 Months

- 4 Months 5/28-9/26

- 11/27

- Del COR-1 A

- 3/4

- Del COR-1 B

- 9/1

- All COR ICD’s

- 9/28

- COR-1 Mass Model Dev

- 4/25

- COR-2 Dsgn Pkg

- F

- 4/22

- COR-2 Flt Inst H/W to NRL

- 3/29

- Begin COR-1 SICM/ICD Dev

- 4/2

- Begin HI Structure Dsgn

- 5/28

- Del HI FM 1/2

- 4/22

- FM Envir Testing

- Rec COR-2 A/B

- 11/14

- 5/28

- Rec HI FM 1/2

- 6/25

- EUVI Structural
- Model Detailed Dsgn

- 2/12

- Ship EUVI/GT/MEB/GSE to NRL

- 1

- 3/31

- 2

- GT Detailed Dsgn

- 11/19

- GT Flt Ready

- 12/9

- 10/24

- 1

- 2

- FLT EUVI 1 Ready

- 1/16

- FLT EUVI 2 Ready

- Assy EUVI Telescope Flt 1

- 5/20

- 10/8

- MEB #1

- Del COR-2 A/B

- 11/14

- 3/1

- Begin Prel Dsgn

- Begin EM Structure Mfg

- 5/3

- 1/7

- Del SCIP FM-A Structure to NRL

- 2/9

- 3/7

- EM Structure to NRL

- 8/18

- 12/10-13

- 11/5-22

- SECCHI Dev / Integration & Test

- 12/08

- 1

- 2

- Del SEB Units to SECCHI

- 4/23

- SEB NRL Ramp-Up

- Begin Finalizing
- Mech Dwgs

- 3/12

- 1/16

- EUVI Shutters

- 10/8

- MEB #1

- 11/26

- MEB #2

- 3/01

- SYS ENG

- 6/27

- Rec All CCD’s

- 11/5-6

- CDR

- 6/12

- CEB’s Avail

- SECCHI FM A/B Deliveries

- 7/8

- 10/12

- 1

- 3 Months

- SECCHI

- 3 Months 7/8 – 10/11

- SECCHI FM-A Available for Delivery

- B

- 3/9

- A

- Begin SEP Development

- SWEA FM2 to UCB

- 12/1

- 1/1

- SWEA FM2

- 5/25

- 11/23

- PLASTIC
- Deliveries

- 9/30

- SWAVES
- Deliveries

- 2

- 1

- 11/08

- Flt S/W Earth Acq Mode BLD 3

- FL S/W G&C BLD 3

- DSAD’s/Reaction Wheel/Star Tracker/IMU A/B to S/C

- 12/31

- 12/2

- DMRD

- F

- Integ Instruments

- SW

- P

- Flt ESA2 Del from Bern

- IM

- 12/14

- SE

- 1

- 2

- Ship to

- 2/18

- 5/26

- 4/13

- 2/4

- 12/15

- Ship to GSFC

- 7/15

- 7/14

- 20 Days

- 8/12

- Begin Launch Operations

- Launch

- SWEA ICD Draft

- 3/6

- 9/3-SWEA GSE Test Equip

- 7/5

- SWEA ETU Assy/Test

- 12/1

- 6/01

- Begin S/W Dev

- 2/27

- Flt S/W Bld 1

- 11/7-8

- CDR

- 12/3-6

- 5/16

- Flt S/W Bld 4

- CA

- 12/7

- Rev

- 1/1

- 9/26

- IMPACT FM1/2
-      Deliveries

- 6/11

- HET Del to Caltech

- SEPT Del to Caltech

- SIT Del to Caltech

- Battery Delivery to I & T

- 10/1 - 10/28

- 8/25

- 9/24

- Contingency

- 1

- 2

- Detailed Thermal Dsgn

- Final FL S/W Doc

- 10/01

- Del S/W Simulator

- 11/4

- CEB’s Avail

- Del Flt FPA’s

- SEP /

- 11/8

- 2

- 8/10

- 1

- 2

- SECCHI FM-B Available for Delivery

- 5/28-9/26

- 6/23

- 5/28

- 9/27

- 7/23

- FM 1 Available for Delivery

- FM 2 Available for Delivery

- PLASTIC

- Instruments Available for Delivery

- 6/29-8/24

- 9/10

- 8/10

- 7/30

- 9/10

- 9/1

- 2

- 1

- 9/15

- FM 1/2 Avail for Delivery

- 8/16

- IMPACT

- 15 Days 8/24-9/15

- 2/23

- 1/26-2/24

- 6/28-7/19

- DSN Van Tests

- 6/17

- EM LGA/HGA Avail

- 11/27

- 5/23

- Prel Structure Analysis

**- Mission Contingency**

**OBS-CC 007**

- 8/25

- 12/10

**S/C-G&C 002**

**OBS-EMI 005**

**OBS-MAG 009**

- LET to UCB for EMC

- IMPACT FM1/2
-     Final I & T

- 5/30

**IMP-BOOM 003**

- 9/30

**SEC-COR-1 011**

- 1/2

**SEC-HI 010**

**OBS-REL 001**

**OBS-RES 004**

- Mission

**ETU’s Complete**

**OBS-PART 006**

**- Risk Trigger Event**

**Overseas**
**Deliveries**

**INST-H/W 008**

- 11/1

**Overseas**
**Deliveries**

**INST-H/W 008**

- 12/11

**Overseas**
**Deliveries**

**INST-H/W 008**

- 8/24

- 9/11

- SEP
- PDR

- LET Env Test

- Phase C/D Det. Design Analysis Dev. Comp.

- Del SCIP FM-B Structure to NRL

- Propul Vendor CDR

- 3/8

- FM1/2 SEP to UCB

## STEREO MASTER SCHEDULE ACRONYM LIST

**2** – Instrument # 2
**2ndy** – Secondary
**A** – Instrument # 1
**Acq** – Acquisition
**Alive** – Aliveness
**APL** – Applied Physics Laboratory
**Assy** – Assembly
**Avail** – Available
**B** – Instrument # 2
**BB** – Bread Board
**Bld** – Build
**CA** – Confirmation Assessment
**CC** – Contamination Control** **
**CCD** – Charged Coupled Device
**C&DH** – Command & Data Handling
**CEB** – Camera Electronics Box
**CoDR **– Conceptual Design
**Comm** – Communications
**Comp** – Components
**Conf** – Confirmation
**COR-1** – Coronograph – 1
**COR-2** – Coronograph – 2
**Del** – Deliver
**DEV** – Development
**Doc** – Document
**DPU **– Data Processing Unit
**DSAD** – Digital Solar Aspect Detectors
**Dsgn** – Design
**DSN** – Deep Space Network
**Elect** – Electronics
**ENG** – Engineering
**EM **– Engineering Model
**EMC **– Electro Magnetic Compatibility
**ESA** – European Space Agency
**ETU** – Engineering Test Unit
**EUVI **– Extreme Ultraviolet Imager
**F** – Final
**Fab** – Fabrication
**Flt **– Flight

**FM** – Flight Model
**FOR** – Flight Operations Review
**FPA **– Focal Plane Assembly
**FPGA **–** **Field Programmable Gate Array
**FRR** – Flight Readiness Review
**G&C** – Guidance & Control
**GS** – Ground System
**GSE** – Ground Support Equipment
**GSFC** – Goddard Space Flight Center
**GT** – Guide Telescope
**HI** – Heliospheric Imager
**HGA** – High Gain Antenna
**H/W** – Hardware
**I** – IMPACT
**ICD** – Interface Control Document
**IDPU **– Instrument Data Processing Unit
**IEM** – Integrated Electronics Module
**IMPACT **– In-situ Measurement of Particles
-   and Coronal Mass Ejection Transients
**IMU** – Inertial Measurement Unit
**Inst** – Instrument
**Integ** – Integration
**I & T** – Integration & Test
**LGA** – Low Gain Antenna
**LRR** – Launch Readiness Review
**LVC** – Low Voltage Converter
**LVPS** – Low Voltage Power Supply
**Mdl** – Model
**MEB **– Mechanisms Electronics Box
**Mech** – Mechanical
**Mfg** – Manufacturing
**Mgmt** – Management
**MM** – Mass Model
**MOR** – Mission Operations Review
**NASTRAN - **NASA Structural Analysis Program
**NRL** – Naval Research Laboratory
**OBS** – Observatory
**P** – PLASTIC
**PDR** – Preliminary Design Review
**PDU **– Power Distribution Unit

**PER** – Pre-Environmental Review
**Pkg** – Package
**PLASTIC** – Plasma and Suprathermal
-   Ion and Composition
**Prel** – Preliminary
**Proc** – Procurement
**Prop** – Proposal
**Propul** – Propulsion
**PSE** – Power Switching Electronics
**PSR** – Pre-Ship Review
**PWR** – Power
**Rev** – Review
**RF** – Radio Frequency
**RIU **–** **Remote Interface Unit
**SA** – Solar Array
**S/C** – Spacecraft
**SCIP** – Sun Centered Instrument Platform
**SE** – SECCHI
**SEB** – SECCHI Electronics Box
**SECCHI **– Sun-Earth Connection Coronal
-   and Heliospheric Investigation
**SEM **– Space Engineering Mechanical (Group)
**SICM **– SECCHI Interface Coordination Memo
**SN1 **– Serial Number 1
**SN2 **– Serial Number 2
**Spec** – Specification
**SRR** – System Requirements Review
**STE **–** **A STEREO Experiment
**Struct** – Structural
**SW** – SWAVES
**S/W** – Software
**SWAVES** – STEREO Waves
**SYS** – System
**Ther** – Thermal
**TWTA** – Traveling Wave Tube Assembly
**UCB** – University of California, Berkeley
**UNH** – University of New Hampshire
**Vib** – Vibration
**VLSI **– Very Large Scale Integration

**STEREO MASTER SCHEDULE ACRONYM LIST**

## Detailed Technical Data

- The legal and policy guidance which the Project Office has received is that unless the data is both satisfactorily extensive in scope and detailed in nature that the component could be *reproduced from *the information provided, without substantial additional design, the export should be considered to fall within the classification of "non‐detailed" technical data.

## Technology Readiness Levels

| TRL | Definition |
| --- | --- |
| 1 | Basic principles observed |
| 2 | Conceptual design formulated |
| 3 | Conceptual design tested analytically or experimentally |
| 4 | Critical function/characteristic demonstrated |
| 5 | Component breadboard tested in relevant environment |
| 6 | Prototype/engineering model tested in relevant environment |
| 7 | Engineering Model tested in space |
| 8 | Full operation capability |

## COR1 Testing Overview

|  | Scheduled
Completion | Actual
Completion | 
Remarks |
| --- | --- | --- | --- |
| Model radiometry | Mar 2000 | Apr 2000 | S/N ~10 required scattering 10-6 BSun |
| Scattering (BTDF) component testing | Sep 2000 | Oct 2000 | Test procedures developed for prototype flight lenses |
| Micro-roughness measurement | Sep 2000 | Oct 2000 | Zygo interferometry measurements on prototype flight lenses |
| Scattered light analytical model | Sep 2000 | Oct 2000 | ASAP and APART models developed with micro-roughness and contamination effects |
| Breadboard Test #1 | Jan 2001 | Feb 2001 | Verified test procedures; verified effective micro-roughness |
| Breadboard Test #2 | Apr 2001 | Jun 2001 | Demonstrated stray light levels exceeded flight requirements |
| Solar Wind Erosion Testing | Jun 2001 | Jun 2001 | Exposed optical flats to solar wind protons at accelerator; no additional scattering found in BTDF testing |
| Vibration Test | Jul 2001 | Aug 2001 | Prototype occulter-field lens assembly tested successfully in excess of flight requirements |
| Thermal-Vac Test | Sep 2001 | Nov 2001 | Verified thermal prediction model |
| ETU optical performance testing | Sep 2002 |  | Alignment/assembly procedures complete.  Verification to be performed in ETU testing. |
| ETU vibration and mass properties | Jul 2002 |  | Structural models complete. Verification to be performed in ETU testing. |
| Verify Contamination Budget | Sep 2002 |  | Analytical model complete.  Verification to be performed in ETU testing. |

## HI Testing Overview

|  | Scheduled
Completion | Actual
Completion | 
Remarks |
| --- | --- | --- | --- |
| SCIP (PDR Level) Thermal Design/Modeling/Analysis |  | 9/14/01 | Preliminary design evaluation |
| HI-1 Breadboard Stray light Rejection (in Air)
 |  | Dec 2001 | Demonstrated stray light levels exceeded flight requirements |
| HI-2 Breadboard  Stray light Rejection (Vacuum) | May 2002 |  | To demonstrate Specified stray light levels could be met in flight |
| HI-1 Breadboard  Stray light Rejection (Vacuum) | May 2002 |  | To demonstrate Specified stray light levels could be met in flight  |
| SCIP (CDR Level) Thermal Design/Modeling/Analysis | 6/21/02 |  |  |
| EQM Forward Baffle initial Stray light testing | 5/17/02 |  |  |
| EQM Initial Optical Test | 7/24/02 |  |  |
| EQM Vibration testing | Aug 1, 2002 |  |  |
| EQM optical performance testing | October 31, 2002 |  |  |
| EQM EMC testing | 1/15/2003 |  |  |
| Thermal Vac testing | 2/24/03 |  | . |
|  |  |  |  |

## COST Estimate Methodology Formulation

- Payload and spacecraft received a high percent of the total mission lifecycle for the Formulation phase (20%)
- Reduced risk on design complexity
- Allowed for early design validation of some design elements on the SECCHI suite (SCIP package, COR1)
- STEREO formulation phase longer than traditional formulation phase
- STEREO schedule stretched in response to Solar-B & TIMED cost impacts

## Cost Estimate Methodology Spacecraft (Continued)

- Non-Recurring Cost Savings
- MESSENGER is a sister mission to STEREO developed at APL
- MESSENGER is using TIMED heritage for the design of their integrated electronics box
- STEREO is sharing non-recurring costs of their new designs with MESSENGER
- STEREO will directly benefit of development effort carried by these two APL missions, scheduled for completion prior to STEREO.

## Spacecraft Design Commonality

**Spacecraft Design Commonality**

**Notes:**
C&DH: 		50% -60% reuse of design and 30% of code
G&C: 		30%  reuse of design and 10% of code
Earth Acq: 	60 % reuse of design and 25% of code
Boot:  		40 % reuse of design and 25% of code

## APL Phase C/D Cost History

- Phase C/D recent program cost history data percent growth from initial cost  estimate
-  		_**Program**_**	****	****	****        **_**Cost Growth**_
- NEAR				(-) 7%
- ACE				(-) 10%
- TIMED (without launch delay)		(+) 7%
- CONTOUR			0% (cost to completion estimate)
- APL’s proposal states that their historical performance is within ± 8% for phase C/D estimates generated at the end of Preliminary Design Review.

- (-) indicates returned funds
- (+) indicates cost growth beyond original cost estimate

## Cost Estimate Methodology Payload

- SWAVES (single instrument)
- SWAVES is a copy of  WIND/WAVES.  Estimate is real year dollar update from actuals
- 60% of the development is provided by foreign contributor.  Their funding and schedule are ahead of the formulation phase
- SECCHI (suite)
- Cost actuals from SOHO/LASCO coronagraphs, TRACE extreme ultraviolet disk imager and guide telescope
- Recent bottoms-up performed by project, code 600 and AETD team supports the allocated budget

## IMPACT/PLASTIC
Estimate used TRIANA solar wind plasma and detection experiment and TRIANA magnetometer
ISTP solar energetic particle experiments
Cost consistent with Technical, Management, and Cost team (TMCO) during AO proposal evaluation

- Estimate used TRIANA solar wind plasma and detection experiment and TRIANA magnetometer
- ISTP solar energetic particle experiments
- Cost consistent with Technical, Management, and Cost team (TMCO) during AO proposal evaluation

**Cost Estimate Methodology Payload (Continued)**