Attachment B Draft_493.0-00XXX_SWO_COR_SPEC_08242022_v1.pdf

Effective Date: TBD

Expiration Date: TBD e

DRAFT

Space Weather (SW) Next

Coronagraph Requirements Specification

U.S. Department of Commerce (DOC)

National Oceanic and Atmospheric Administration (NOAA)

NOAA Satellite and Information Service (NESDIS)

National Aeronautics and Space Administration (NASA)

Space Weather Observations (SWO) Program

SWO CMO

<Date>

Released

Space Weather Next Lagrange 1 (NEXT) Project, Code 493.0

493-xxxx, Revision –

SW Next Coronagraph Req Spec 490.0-XXXXX, Revision – ii

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SW Next Coronagraph Requirements Specification

Review/Signature/Approval Page

Prepared by:

TBD

SWO Instrument Systems Manager

NASA Goddard Space Flight Center

Reviewed by:

SWO Program System Engineer

Date

SWO Deputy Program Director

Chief, Project Management and Execution Division

NOAA NESDIS/OPPA

Approved by:

SW NEXT Project Manager

Electronic Approval available on-line at: Windchill (nasa.gov) iii

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Preface This document is under SWO Program Division configuration control. Once this document is approved, approved changes are handled in accordance with Class I and Class II change control requirements as described in the SWO Configuration Management Procedure, and changes to this document shall be made by complete revision.

In this plan, all mandatory actions (i.e., requirements) are denoted by statements containing the term “shall.” The terms “may” or “can” denote discretionary privilege or permission; “should” denotes a good practice and is recommended but not required; “will” denotes expected outcome;

and “are/is” denotes descriptive material.

Any questions should be addressed to:

SWO Configuration Management Office

NASA/GSFC

Code 490.0

Greenbelt, MD 20771 iv

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Change History Log

Revision Effective Date Description of Changes

(Reference the CCR & CCB/ERB Approval Date)

Rev - TBD This is the initial baselining of the document. The document will be placed under CM control upon receipt of all required approvals.

v

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Table of Contents

1 INTRODUCTION

1.1 General Information

1.2 Scope

2 APPLICABLE DOCUMENTS

3 CONTRACT DESCRIPTION

3.1 Coronagraph Description

3.2 Ground Support Equipment Description

4 FUNCTIONAL/PERFORMANCE REQUIRMENTS

4.1 Coronagraph Performance Requirements

4.1.1 Scene Coverage

4.1.2 Spatial Resolution

4.1.3 Accuracy

4.1.4 Field of View (FOV)

4.1.5 Refresh Rate and Latency

4.1.6 Detector Well Depth

4.2 Resource Allocations

4.2.1 Mass

4.2.2 Physical Envelope

4.2.3 Operational Power

4.2.4 Peak Operational Power

4.2.5 Survival Heater Power

4.2.6 Telemetry

4.2.7 Transient Magnetic Field

4.2.8 Static Magnetic Field

4.3 Operational Requirement

4.3.1 Mode Transitions

4.3.2 Deterministic Power on Configuration

4.3.3 Safe Mode

4.3.3.1 Entry Into Safe Mode

4.3.4 Normal Operational Mode

4.3.5 On-Orbit Operations

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4.3.6 Station Keeping

4.4 Power

4.4.1 Voltage Range

4.4.2 Abnormal Voltages

4.4.3 Power Transients

4.4.4 Sudden Removal of Power

4.4.5 Over-Current Protection

4.4.6 Primary Power Return Ground

4.4.7 Turn On Current Transients

4.5 Electrical Grounding

4.6 Signal and Data Interfaces

4.6.1 Passive Analog Telemetry

4.6.2 Data Signal Interface

4.6.2.1 Telemetry Source Packet Format

4.6.2.2 Command Source Packet Format

4.6.3 Clock Signal Interface

4.7 Flight Software

4.7.1 Flight Load Non-volatile Memory

5 ENVIRONMENTAL REQUIREMENTS

5.1 Quasi Static Acceleration

5.2 Frequency Requirement

5.2.1 Fundamental Launch Frequencies

5.3 Vibration

5.3.1 Sinusoidal Vibration

5.3.2 Random Vibration

5.4 Shock

5.5 Acoustics

5.5.1 Maximum Depressurization Rate

5.5.2 Launch Vehicle (LV) Environmental Control System (ECS) Impingement

5.6 On-Orbit Dynamic Environment

5.7 Thermal Requirements

5.7.1 Flight Interface Design Temperature Limits

5.8 Charged Particle Radiation Requirements

5.8.1 Definitions

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5.8.2 NON-Destructive Events (SEUs, SETs, SEFIs, SHEs, and MBUs)

5.8.3 Destructive Events

5.8.3.1 Single Event Latchups (SELs)

5.8.3.2 Single Event Gate Rupture (SEGRs), Single Event Burnout (SEB)

5.8.4 Charging Environment

5.8.5 Total Ionizing Dose

5.8.6 Enhanced Low Dose Rate Sensitivity (ELDRS)

5.8.7 Displacement Damage Dose

5.9 Electromagnetic Compatibility

5.9.1 Conducted Emissions

5.9.1.1 CE101-Differential Mode Current Emission Limits

5.9.1.2 CE03 – Differential Mode Current Emission Limits

5.9.1.3 CMBCE - Common Mode Bulk Conducted Emissions Limits

5.9.2 Conducted Susceptibility

5.9.2.1 CS101 – Conducted Susceptibility, Power Leads

5.9.2.2 CS114 Conducted Susceptibility Differential Mode Power Leads

5.9.2.3 CS114 – Conducted Susceptibility, Common Mode, Power and Signal Cables . 21

5.9.2.4 CS06 - Conducted Susceptibility, Transients, Power Leads

5.9.2.5 CS06 - Conducted Susceptibility, Bulk Cable Injection, Impulse Excitation, Interconnecting Cables

5.9.3 Radiated Emissions

5.9.3.1 RE102 Radiated Emissions Electric Field

5.9.4 Radiated Susceptibility

5.9.4.1 RS103 - Radiated Susceptibility, Electric Field Launch

5.9.4.2 RS103 - Radiated Susceptibility, Electric Field, On-Orbit

6 CONTAMINATION CONTROL

6.1 COR Surface Cleanliness Requirements

6.2 The Coronagraph Instrument shall exceed 300R5E-1 (TBR) at delivery to observatory for integration. Contamination Generation

6.3 The Coronagraph Instrument materials shall have less than 1% TML and less than 0.1%

CVCM. Electrostatic Cleanliness

6.3.1 Conducted Surface Ground Path

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6.3.2 Conducted Surface Resistivity

6.3.3 Closeout of Gaps and Apertures

6.3.4 Exposed Harness Specific Requirements

6.3.5 Thermal Blankets

7 DESIGN & CONSTRUCTION REQUIREMENTS

7.1 Workmanship

7.1.1 Connectors

7.2 Reliability and Mission Lifetime

7.2.1 Mission Life

7.2.2 Operating Time

7.2.3 Trouble Free Time

7.3 Ground Handling

7.3.1 Ground Support Equipment (GSE) Design

7.3.2 Lifting Hardware

7.3.3 Manual Lifting Hardware

7.3.4 GSE Cleanliness

7.3.5 GSE Bakeout

7.3.6 Test Harness

8 LOGISTICS

8.1 Ground Support Equipment

8.1.1 Electrical System Test Equipment

8.1.2 Coronagraph Emulator

8.2 Transportation Equipment

8.2.1 Shipping Container

List of Figures

Figure 4-1. Telemetry Source Packet Definition

Figure 4-2. Command Source Packet

Figure 5-1 Shock Environment

Figure 5-2 Launch Vehicle Acoustics

Figure 5-3 Total Ionizing Dose-Depth Curve for a 7-year Mission at L1

Figure 5-7 Common Mode Bulk Conducted Emissions Limit ix

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List of Tables

Table 5-1. COR Design Limit Loads (TBR)

Table 5-2 Maximum Sine Vibration Environment (TBR)

Table 5-3 Random Vibration Environment (TBR)

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1 INTRODUCTION

1.1 General Information

1.2 Scope

This specification describes the performance and electrical, mechanical, environmental, and verification testing requirements for a space-qualified Coronagraph for the Space Weather Next

Program.

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2 APPLICABLE DOCUMENTS

The following documents and drawings in effect on the day this specification was signed shall apply to the fabrication and to the electrical, mechanical, and environmental requirements of the

Coronagraph to the extent specified herein. In the event of conflict between this specification and any referenced document, this specification will govern, except for the SW Next Coronagraph

Statement of Work (SOW), in which case the Statement of Work takes precedence.

The following is a list of the applicable specifications and publications

Table 2-1. Applicable Documents

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3 CONTRACT DESCRIPTION

3.1 Coronagraph Description

TBD.

The Coronagraph contract includes the delivery of two (2) (TBD) flight model (FM) instruments and one (1) Engineering Development Unit (EDU), flight harness(es) between instrument boxes, if applicable, and enough spares and built-up sub-assemblies for two (TBD) additional FM.

3.2 Ground Support Equipment Description

The Coronagraph contract includes the delivery of (2) sets of the Electrical System Test Equipment

(ESTE), (3) Coronagraph Emulators, (1) Flight Software Development Environments (FSDEs), and

(1) One Ground Processing Development System (GPDS). Additionally, Mechanical Ground

Support Equipment (MGSE) such as lifting fixtures/handles, shipping containers, purge carts, drill templates, test fixtures, non-flight protective covers, etc. are included in the delivery. Electrical

Ground Support Equipment includes, but is not limited to, test cables and break-out boxes as required.

Ground Support Equipment is necessary to operate the instrument during spacecraft testing.

Supplying this equipment is considered part of the delivery for the instrument. More information is provided in the contract deliverable requirement list (CDRL).

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4 FUNCTIONAL/PERFORMANCE REQUIRMENTS

This section defines the functional and performance requirements for the Coronagraph.

The requirements in this Specification pertain to the Coronagraph ‘system’, which may include all instrument hardware, software, and ground processing algorithms. The Coronagraph contractor is not responsible for the operational ground system, but certain specifications will require ground processing after collection but before data distribution for which the contractor is responsible for defining.

4.1 Coronagraph Performance Requirements

4.1.1 Scene Coverage

The Coronagraph shall capture radial coronal scenes from ≥ 3 RSun to ≤ 22 RSun.

The Coronagraph shall capture the radial coronal scene in a continuous 290° polar scene coverage satisfying all spatial and photometric requirements, with a goal of 360°.

Rationale: 290° allows use of pylon to support occulter.

4.1.2 Spatial Resolution

The Coronagraph shall capture coronal image with spatial resolution ≤ 70.0 arcsec.

Where The image spatial resolution is defined as the average of the optical spatial resolution in the sagittal and tangential planes of the optical system. The spatial resolution is defined as the distance, in arcsec, between two point sources of equal brightness located at infinity. The relative intensity between the peaks of the imaged sources (100% intensity) and the intensity at the mid-point between the peaks, shall be 90% or less.

4.1.3 Accuracy

The Coronagraph shall have photometric accuracy for the corona image of ≤ 10% during S4 Solar Storm.

4.1.4 Field of View (FOV)

The Coronagraph clear field of view shall be less than 50 deg (TBR) half cone angle.

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4.1.5 Refresh Rate and Latency

The Coronagraph shall produce an image during nominal operations every 15 min or less.

The Coronagraph shall produce an image within 15 minutes after end of image acquisition.

4.1.6 Detector Well Depth

The Coronagraph instrument exposure time shall be such that total brightness measurement in electrons does not exceed 95% full well of detector.

4.2 Resource Allocations

4.2.1 Mass

The Coronagraph instrument, including the sensor unit, electronics box, sensor standoff bracket (if required), intra-instrument harness, and thermal blankets, shall have a combined mass of less than or equal to 30 kg (TBR).

4.2.2 Physical Envelope

The Coronagraph instrument volume (length*width*height), including the sensor unit (TBD), electronics box (TBD), mounts, sensor standoff bracket (if required), instra-instrument harness, thermal blankets, and connectors, for both stowed and operational configurations shall have dimensions that do not exceed a total volume of TBD cm3. These dimensions pertain to both static and dynamic envelopes of the instrument.

The Coronagraph maximum instrument volume during deployment of mechanisms shall have dimensions that do not exceed a total volume of TBD cm3

4.2.3 Operational Power

The Coronagraph instrument average operational power shall not exceed 29 Watts when averaged over any 15-minute period.

4.2.4 Peak Operational Power

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4.2.5 Survival Heater Power

The Coronagraph instrument survival heater power shall not exceed TBD Watts when averaged over any 60-minute period.

4.2.6 Telemetry

The Coronagraph instrument total data rate, including all overhead associated with Consultative

Committee for Space Data Systems (CCSDS) packetization by the instrument at the spacecraft interface, shall not exceed 60 kbits per second (TBR) averaged over any 15-minute period.

4.2.7 Transient Magnetic Field

The Coronagraph instrument shall limit varying magnetic field less than 5 Hz to less than 4 nT zero-to-peak in any axis 1 meter from any face of the unit for any operating mode and changing configurations.

4.2.8 Static Magnetic Field

The Coronagraph instrument shall limit the static magnetic field to less than 40 nT in any axis 1 meter from any face of the unit for any operating mode.

4.3 Operational Requirement

4.3.1 Mode Transitions

The Coronagraph instrument shall transition from the current mode to any other mode without causing damage to itself.

4.3.2 Deterministic Power on Configuration

The Coronagraph instrument shall initialize into a predetermined configuration.

4.3.3 Safe Mode

The Coronagraph instrument shall provide a Safe Mode. Safe mode is an operating mode of the instrument during which all non-essential subsystems are shut down and only essential functions are

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The Coronagraph instrument shall be capable of remaining in a safe configuration for at least 120 hours without ground intervention.

4.3.3.1 Entry Into Safe Mode

The Coronagraph instrument shall enter Safe Mode upon detection of internal faults that can cause damage to the instrument.

4.3.4 Normal Operational Mode

In normal operational mode, the Coronagraph instrument shall be in a fully functional configuration in which designed measurements are made in accordance with the performance requirements listed in section 4.1 of this document and are available to be sent to the spacecraft for downlink.

4.3.5 On-Orbit Operations

4.3.6 Station Keeping

The Coronagraph instrument shall continuously operate during all spacecraft maneuvers.

The Coronagraph instrument may not meet performance requirements during these maneuvers but shall meet them again after each maneuver is completed within 300 secs.

4.4 Power

4.4.1 Voltage Range

The Coronagraph instrument shall operate over the bus voltage range of 30 +/-4 VDC (TBR) at the primary power inputs during all normal mission phases and for all expected load conditions (except when turned off).

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4.4.2 Abnormal Voltages

The Coronagraph instrument shall survive without performance degradation after indefinite exposure to an anomalous voltage range of 0 to +40 VDC.

4.4.3 Power Transients

The Coronagraph instrument meet its performance requirements in the presence of transients specified in MIL-STD-461F, Figure CS115-1 and Figure CS116-2.

4.4.4 Sudden Removal of Power

The Coronagraph instrument shall meet its performance requirements without degradation after exposure to an abrupt, unannounced removal of power.

4.4.5 Over-Current Protection

The Coronagraph instrument does not use non-resetting over-current protection (i.e., fuses) internal to the unit

4.4.6 Primary Power Return Ground

The Coronagraph instrument shall provide a dedicated Primary Power return in the same connector as the primary power.

4.4.7 Turn On Current Transients

The Coronagraph instrument shall limit any change in operational power current at any time

(including initial power turn-on) to no more than 0.2A/µs. (TBR)

4.5 Electrical Grounding

The Coronagraph instrument primary power interfaces, primary power and primary power returns, shall be isolated from the unit chassis by a DC resistance of greater than or equal to 10 Megaohms.

The Coronagraph instrument survival heater power interfaces shall be isolated from the unit

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The Coronagraph instrument Secondary power inputs shall be isolated from primary power by a DC resistance of greater than 10 Megaohms.

The Coronagraph instrument shall reference its secondary returns (power and signal grounds) to the unit chassis ground.

4.6 Signal and Data Interfaces

4.6.1 Passive Analog Telemetry

The Coronagraph instrument shall utilize no more than 6 (TBR) analog signals to monitor critical temperature points when the Magnetometer is powered off.

4.6.2 Data Signal Interface

The Coronagraph instrument shall interface for data transfer to or from the spacecraft by SpaceWire

(ECSS-E50-12A)

4.6.2.1 Telemetry Source Packet Format

The Coronagraph instrument shall transfer all data to the spacecraft using the CCSDS 133.0-B-1

Section 4.1 Protocol Data Unit definition shown in the Telemetry Source Packet Definition Figure

4-1

Figure 4-1. Telemetry Source Packet Definition

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The Coronagraph instrument telemetry Source packets shall have a maximum data zone of 8192 octets including Secondary Header.

4.6.2.2 Command Source Packet Format

The Coronagraph instrument shall receive all data from the spacecraft formatted per CCSDS 133.0-

B-1 Section 4.1 Protocol Data Unit definition shown in the Command Source Packet Definition

Figure 4-2.

Figure 4-2. Command Source Packet

The Coronagraph command Source packets shall be variable length with a maximum data zone of

8192 octets.

4.6.3 Clock Signal Interface

4.7 Flight Software

4.7.1 Flight Load Non-volatile Memory

The Coronagraph flight software image shall be contained in its entirety in non-volatile memory at launch.

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5 ENVIRONMENTAL REQUIREMENTS

Environmental design requirements for the COR Instrument are specified in this section.

5.1 Quasi Static Acceleration

Quasi-static acceleration represents the combination of steady-state accelerations and the low frequency mechanically transmitted dynamic accelerations that occur during launch.

The Coronagraph instrument shall withstand the quasi-static design limit loads defined in the mass-acceleration curve (MAC) shown in Table 5-1 without damage or degradation of performance and are to be applied one axis at a time. The design loads shown below will be updated based on the results of coupled loads analysis.

Table 5-1. COR Design Limit Loads (TBR)

Mass (kg) Limit Load (g)

1 41.3

5 42.4

10 36.6

20 30.3

40 24.2

5.2 Frequency Requirement

5.2.1 Fundamental Launch Frequencies

The Coronagraph instrument individual units shall have a fundamental frequency greater than 75Hz when hard mounted at its spacecraft interface.

5.3 Vibration

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5.4 Shock

The Coronagraph instrument shall meet its performance requirements after being exposed to the proto-flight shock environment defined by the separation system in Figure 5-1. TBD

Figure 5-1 Shock Environment

5.5 Acoustics

The Coronagraph instrument shall meet its performance requirements after being exposed to the acoustic loads given in Figure 5-2

Figure 5-2 Launch Vehicle Acoustics

5.5.1 Maximum Depressurization Rate

5.5.2 Launch Vehicle (LV) Environmental Control System (ECS) Impingement

5.6 On-Orbit Dynamic Environment

5.7 Thermal Requirements

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5.7.1 Flight Interface Design Temperature Limits

5.8 Charged Particle Radiation Requirements

Units containing electronic parts will be exposed to a natural space radiation environment that consists of: (1) trapped particles which include electrons, protons, and heavier ions; (2) particles from solar events (coronal mass ejections and flares); and (3) galactic cosmic ray (GCR) particles.

5.8.1 Definitions

Total Ionizing Dose (TID) - the mean energy deposited by ionizing radiation in a device region divided by the mass of the region. This is often given in units of rad(Si), where 1 rad(Si) = 100 erg deposited per gram of silicon.

Enhanced Low Dose Rate Sensitivity (ELDRS) - used to refer to a part that shows enhanced radiation-induced damage at dose rates below 50 rad(Si)/s. The enhancement is the result of true dose rate effects.

Non-Ionizing Energy Loss (NIEL) - a measure of the rate of energy loss due to atomic displacements as a particle traverses a material.

Displacement Damage Dose (DDD) - the mean energy deposited by ionizing radiation in a device region that goes into atomic displacements divided by the mass of the region. There is no official unit for DDD. One such unit is MeV/g.

Single Event Effect (SEE) - any measurable effect to a circuit due to an ion strike. This includes, but is not limited to, single event upsets (SEUs), single event transients (SETs), single hard errors

(SHEs), single event latchups (SELs), single event functional interrupts (SEFIs), single event burnouts (SEBs), single event gate ruptures (SEGRs), and single event dielectric ruptures (SEDRs).

Single Event Upset (SEU) - a change of state or transient induced by an energetic particle such as a cosmic ray or proton in a device. This may occur in digital or analog, circuits and may have effects in surrounding interface circuitry (a subset known as SETs). These are “soft” errors in that a reset or rewriting of the device will usually return the device to normal behavior thereafter. The general goal for non-destructive events such as SEUs or SETs is not to avoid them completely, but to manage

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Single-Event Functional Interrupt (SEFI) - a condition that causes loss of device functionality due to a single event in a control portion of a device. It generally requires a device reset or a re-initialization to resume normal device operations, but for some devices, a power cycle is necessary to resume normal device operations. The general goal for non-destructive events such as SEFI is to avoid them, however, managing their impact through robust circuit design, automatic correction, and/or operational activities may be considered.

Single Hard Error (SHE) - a SEU that causes a permanent change to the operation of a device. An example is a stuck bit in a memory device.

Multiple Bit Upset (MBU) - an event induced by a single energetic particle such as a cosmic ray or proton that causes multiple upsets or transients during its path through a device or system in a single logical structure (ex., 2 bits affected in a single 16-bit word).

Single Event Latchup (SEL) - a condition that may cause device failure due to a single event induced high current state. A SEL may or may not cause permanent device damage, but requires power cycling of the device to resume normal device operations. In addition, susceptible devices have the concern for latent damage (device does not fail from the immediate single particle event, but reliability is degraded and premature failure may occur).

Single-Event Burnout (SEB) - a condition that can cause device destruction due to a high-current state in a power transistor.

Single-Event Gate Rupture (SEGR) - a destructive single ion induced condition in power MOSFETs that may result in the formation of a conducting path in the gate oxide.

Linear Energy Transfer (LET) - a measure of the energy deposited per unit length as an energetic particle travels through a material. The common LET unit is MeV*cm2/milligram (mg) of material.

Threshold LET (LETth) - the maximum LET at which no SEE is observed at a particle fluence of

107 ions/cm2.

5.8.2 NON-Destructive Events (SEUs, SETs, SEFIs, SHEs, and MBUs)

Coronagraph Instrument shall suffer no permanent loss of function due to non-destructive SEUs

The Coronagraph Instrument shall meet all performance requirements during a CREME96 model

Worst Week flux environment with 90% probability. Note: This includes faults requiring ground intervention as well as data errors impacting performance.

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5.8.3 Destructive Events

5.8.3.1 Single Event Latchups (SELs)

Coronagraph Instrument shall have a single-event latchup (SEL) LET threshold greater than 37

MeV-cm2/mg or have a method for autonomous recovery

5.8.3.2 Single Event Gate Rupture (SEGRs), Single Event Burnout (SEB)

Coronagraph Instrument power transistors shall have a SEGR and SEB threshold LET > 37

(MeV·cm2)/mg when biased at 133% of the application Vds or Vce.

5.8.4 Charging Environment

Coronagraph Instrument shall withstand the degradation of surface materials as well as internal charging effects due to the radiation environment for a mission with an orbit about the Sun-Earth first Lagrange point, L1

5.8.5 Total Ionizing Dose

Coronagraph Instrument shall withstand the total ionizing dose (TID) environment for a 7-year mission with an orbit about the Sun-Earth first Lagrange point, L1.

Coronagraph Instrument EEE parts and materials exposed to space shall tolerate a minimum of

TBD Mrad(Si).

Coronagraph Instrument shielded EEE parts and materials shall tolerate 95% confidence level dose-depth curve shown in Figure 5-3 Total ionizing dose-depth curve for a 7-year mission at L1

Figure 5-3 Total Ionizing Dose-Depth Curve for a 7-year Mission at L1

5.8.6 Enhanced Low Dose Rate Sensitivity (ELDRS)

Coronagraph Instrument bipolar or bi-CMOS technology parts shall be immune to Enhanced Low

Dose Rate Sensitivity (ELDRS) effects

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5.8.7 Displacement Damage Dose

Coronagraph Instrument shall withstand the displacement damage dose (DDD) environment for a 7-year mission with an orbit about the Sun-Earth first Lagrange point, L1.

Coronagraph Instrument Silicon EEE parts and materials exposed to space shall tolerate a minimum displacement damage dose of TBD MeV/g.

Coronagraph Instrument shielded Silicon EEE parts and materials shall tolerate 95% confidence level displacement damage dose-depth curve shown in Figure 5-4.

Figure 5-4 Silicon displacement damage dose-depth curve for a 7-year mission at L1

Coronagraph Instrument Gallium Arsenide EEE parts and materials exposed to space shall tolerate a minimum displacement damage dose of TBD MeV/g.

Coronagraph Instrument Shielded Gallium Arsenide EEE parts and materials shall tolerate the 95% confidence level displacement damage dose-depth curve shown in Figure 5-5

Figure 5-5 Gallium Arsenide displacement damage dose-depth curve for a 7-year mission at

L1

5.9 Electromagnetic Compatibility

5.9.1 Conducted Emissions

Conducted emission requirements are designed to prevent excessive noise from being induced on the spacecraft power bus by units that are connected to the bus.

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5.9.1.1 CE101-Differential Mode Current Emission Limits

Coronagraph Instrument shall not produce reflected ripple greater than the CE101 limits from 30 Hz to 150 kHz shown in Figure 5-6 when power leads are tested to a modified MIL-STD- 461F CE101

(extended frequency range) test method as described in GSFC- STD-7000A, section 2.5.2.1.1.

Figure 5-6 CE101/CE1012 (CE03) Differential Mode Limits

5.9.1.2 CE03 – Differential Mode Current Emission Limits

Coronagraph Instrument shall not produce reflected ripple greater than the limits from 150 kHz to

50 MHz, shown in Figure 5-6 when power leads are tested to the MIL-STD-462C CE03 test method as described in GSFC-STD-7000A, section 2.5.2.1.1

5.9.1.3 CMBCE - Common Mode Bulk Conducted Emissions Limits

Coronagraph Instrument Common Mode Bulk Conducted Emissions (CMBCE) from the power and return leads shall not exceed the limits from 30 Hz to 200 MHz in Figure 5-7, referenced to chassis, when tested using an absorbing clamp per GSFC-STD-7000A, Section 2.5.2.1.2.

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Figure 5-7 Common Mode Bulk Conducted Emissions Limit

5.9.2 Conducted Susceptibility

Conducted susceptibility requirements are designed to ensure that any unit connected to the spacecraft power bus is not unduly susceptible to noise expected to be present on the power bus.

5.9.2.1 CS101 – Conducted Susceptibility, Power Leads

The Coronagraph Instrument shall meet performance requirements when power leads are subjected to the limits shown in Figures 5-8 and 5-9, from 30 Hz to 150 kHz per the MIL-STD-461F CS101 test method as described in GSFC-STD-7000A, Section 2.5.2.2.1.

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Figure 5-8 Power Lead Conducted Susceptibility (CS101) Voltage Limit

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Figure 5-9 Conducted Susceptibility Power Limit (30 Hz to 150 kHz)

5.9.2.2 CS114 Conducted Susceptibility Differential Mode Power Leads

The Coronagraph Instrument shall meet performance requirements when high side power leads are subjected to an injection probe drive level of 83.5 dBμA over a frequency range of 150 kHz - 50

MHz per the MIL-STD-461F CS114 test method as defined in GSFC-STD-7000A, Section

2.5.2.2.4.2.

5.9.2.3 CS114 – Conducted Susceptibility, Common Mode, Power and Signal Cables

The Coronagraph Instrument shall meet performance requirements when power and signal cables are subjected to an injection probe drive level of 70 dBμA over a frequency range of 10 kHz to 200

MHz per the MIL-STD-461F CS114 test method (Common Mode) as defined in GSFC-STD-

7000A, section 2.5.2.2.4.1.

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5.9.2.4 CS06 - Conducted Susceptibility, Transients, Power Leads

5.9.2.5 CS06 - Conducted Susceptibility, Bulk Cable Injection, Impulse Excitation, Interconnecting Cables

5.9.3 Radiated Emissions

Radiated emission requirements are designed to prevent excessive noise from being radiated by the spacecraft units

5.9.3.1 RE102 Radiated Emissions Electric Field

The Coronagraph Instrument electric field emissions shall not exceed the limits of TBD when tested per the MIL-STD-461F RE102 test method as defined in GSFC-STD-7000A, section 2.5.2.3.2

5.9.4 Radiated Susceptibility

5.9.4.1 RS103 - Radiated Susceptibility, Electric Field Launch

The Coronagraph Instrument shall survive without performance degradation after being irradiated with electric field of 20 V/m from 2 MHz to 18 GHz when tested per the MIL-STD-461F RS103 test method as defined in GSFC-STD-7000A, section 2.5.2.4.2 in the off state (i.e., launch configuration)

5.9.4.2 RS103 - Radiated Susceptibility, Electric Field, On-Orbit

The Coronagraph Instrument shall not exhibit any malfunction, degradation of performance as a result of being irradiated with electric field of 2 V/m from 2 MHz to 18 MHz when tested per the

MIL-STD-461G 461F RS103 test method as defined in GSFC-STD-7000A, section 2.5.2.4.2 while powered on and in most sensitive operating mode.

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6 CONTAMINATION CONTROL

The information in this section addresses the cleanliness requirements for the Coronagraph instrument so that the Coronagraph instrument performance will still be in compliance with requirements at the end of the designed mission life, and the Coronagraph instrument will not be a contamination threat to other instruments and the spacecraft. For this mission, the most contamination sensitive instruments will generally dictate the contamination requirements for other instruments and the spacecraft.

6.1 COR Surface Cleanliness Requirements

6.2 The Coronagraph Instrument shall exceed 300R5E-1 (TBR) at delivery to observatory for integration. Contamination Generation

6.3 The Coronagraph Instrument materials shall have less than 1% TML and less than

0.1% CVCM. Electrostatic Cleanliness

The following paragraphs provide requirements and guidelines for minimizing the magnitude and variations in the radiated electric field from the external surfaces of the Coronagraph instrument when exposed to the space plasma. All external unblanketed surfaces that are exposed to the space plasma will be sufficiently conductive as defined below.

6.3.1 Conducted Surface Ground Path

The Coronagraph Instrument external unblanketed surfaces shall be connected to the spacecraft interface with a resistance less than 5 ohms, either through the use of ground wire(s) or through metal-to-metal mounting contact.

6.3.2 Conducted Surface Resistivity

The Coronagraph Instrument external unblanketed surfaces shall have a resistivity less than 108 ohms/square.

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6.3.3 Closeout of Gaps and Apertures

6.3.4 Exposed Harness Specific Requirements

6.3.5 Thermal Blankets

The Coronagraph Instrument multi-layer insulation (MLI) blankets outer layers shall be electrically conductive.

The Coronagraph Instrument MLI blanket conductive layers shall be grounded to the instrument using low resistance wire as specified in Table 6-1.

Table 6-1 Thermal Blanket Area vs. Grounding Tabs

The Coronagraph Instrument MLI blanket shall be connected to spacecraft ground point with electrical resistance less than 10 ohms.

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7 DESIGN & CONSTRUCTION REQUIREMENTS

7.1 Workmanship

7.1.1 Connectors

7.2 Reliability and Mission Lifetime

7.2.1 Mission Life

7.2.2 Operating Time

7.2.3 Trouble Free Time

7.3 Ground Handling

7.3.1 Ground Support Equipment (GSE) Design

7.3.2 Lifting Hardware

7.3.3 Manual Lifting Hardware

7.3.4 GSE Cleanliness

7.3.5 GSE Bakeout

7.3.6 Test Harness

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8 LOGISTICS

8.1 Ground Support Equipment

8.1.1 Electrical System Test Equipment

8.1.2 Coronagraph Emulator

8.2 Transportation Equipment

8.2.1 Shipping Container