Attachment E-1 GXIUIID.pdf

Effective Date: May 13, 2021 418-XO-GXIUIID-0023 Expiration Date: Five years from date of last signature Version 2.1 Responsible Organization: GeoXO Flight Project/Code 418

Geostationary and eXtended Observations

(GEO-XO)

Unique Instrument Interface Document (UIID) Signature page

Prepared by:

Electronically approved by: 05/03/2021

Jemma Kline Date GeoXO Flight Project, Instrument Systems Engineer NASA GSFC, Code 418

Reviewed by:

Electronically approved by: 05/11/2021

Alexander Krimchansky Date GeoXO Flight Project, Mission Systems Engineer NASA GSFC, Code 599

Approved by:

Electronically approved by: 05/13/2021

Jason H. Hair Date GeoXO Flight Project, Project Manager NASA GSFC, Code 418

/GeoXO Flight Project Imager

GXIUIID

418-XO-GXIUIID-0023, RM Version, GeoXO Imager (GXI) Unique Instrument Interface Document (UIID)

Version: 2.1 Printed by: rkhoover Printed on: Wednesday, February 9, 2022

No filter applied.

No sort applied.

Generated from DOORS 9.7.2.4

Contents

1 1Scope

1.1 1Document Overview

1.2 1Requirements Terminology

1.3 2Order of Precedence

2 3Applicable Documents

3 4Allocations

3.1 4Command and Data Handling

3.1.1 4Instrument-to-Spacecraft Science Rate

3.1.2 4Telemetry Data Rate

3.1.3 4Application Process Identifiers

3.1.4 4GEO-XO Reliable Data Delivery Protocol Packet Rate

3.2 4Power

3.2.1 4Average Operational Power

3.2.2 4Maximum Operational Power

3.2.3 4Average Survival Power

3.2.4 4Maximum Survival Power

3.3 5Mechanical

3.3.1 5Mass Properties

3.3.2 5Cabling Between Units

3.3.3 5Volume

3.3.4 5Optical Port Field-of-View

3.3.5 6Radiator Field-of-View (CCR-X00011)

3.3.6 6Field-of-View in the +X direction (CCR-X00039A)

3.3.7 6Mounting

3.4 6Mechanical Disturbances (CCR-X00039A)

3.4.1 6Integrated Angular Momentum

3.4.2 7Angular Momentum Limits

3.4.3 7Instrument Translation Acceleration Limits

3.4.4 9Predicted Interface Force and Torque (PIFT) Responses

3.4.5 10Spacecraft Mounting Stiffness

3.4.6 10External Sourced Translation Acceleration Limits

3.4.7 11Instrument Torque Limit (CCR-X00039A)

3.5 11Thermal

Project: GeoXO Flight Project Imager Module: GXIUIID Baseline Version: 2.1

Contents ii

3.6 11Instrument Purge Requirements

4 12Constraints

5 13GIRD Deviations

6 14Design Verification Requirements

6.1 14Radiated Emissions, Electric Field (RE 102)

6.2 14Radiated Emissions in DCS Receiver Bands

7 16Acronyms

Contents iii

Page 1 of 16 Printed Wednesday, February 9, 2022

ID

GXIUIID1

GXIUIID2

GXIUIID3

GXIUIID4

GXIUIID5

GXIUIID6

GXIUIID7

GXIUIID8

GXIUIID9

GXIUIID10

GXIUIID11

GXIUIID12

Object Number

1.0-1

1.0-2

1.0-3

1.0-4

1.0-5

1.0-6

1.1

1.1.0-1

1.2

1.2.0-1

1.2.0-2

418-XO-GXIUIID-0023, RM Version, GeoXO Imager (GXI) Unique Instrument Interface Document (UIID)

1 Scope The purpose of this Unique Instrument Interface Document (UIID) is two-fold. The first is to allocate GEO-XO series spacecraft resources to the IMAGER. The second is to serve as a core building block on which the IMAGER-spacecraft interface can be designed. The spacecraft integrating contractor and the IMAGER contractor shall meet each of their respective interface requirements as defined in this document.

The Government will be the system integrator until a system performance contractor or spacecraft contractor with that responsibility is selected. Until that time, the Government will be responsible for accommodation trades, resource allocation (weight, power, space, bandwidth, etc.), and resolving interface issues. This UIID will govern the development of an Interface Control Document (ICD) which will be a joint activity of the IMAGER and spacecraft contractors.

The IMAGER ICD establishes the details of the electrical, communications, mechanical, thermal, integration and test, and command and data handling (C&DH) interfaces between the IMAGER instrument and the GEO-XO spacecraft. After the ICD is signed and approved by all parties, the spacecraft contractor shall maintain the ICD.

The IMAGER is a radiometer designed to provide variable area imagery and radiometric information of the Earth’s surface, atmosphere and cloud cover. The instruments collect data on a three-axis body-stabilized satellite in geosynchronous orbit.

Data availability, radiometric quality, simultaneous data collection, coverage rates, scan flexibility, and minimizing data loss due to the sun are prime requirements of the system. The instrument requires primary power and command input data from the spacecraft. Instrument output data to the spacecraft contains instrument information, instrument telemetry and ancillary data.

The sensor units contain the optical system, scanner, detectors and their cooling systems and directly related electronics. The electronics unit contains the power supply module, command, control, and data processing circuitry. If required, an auxiliary electronics unit may be used for active detector cooling.

1.1 Document Overview

Together, the General Interface Requirements Document (GIRD) and the IMAGER UIID establish the IMAGER-spacecraft interface requirements. The GIRD applies to all GEO-XO instruments while the IMAGER UIID is specific to the IMAGER. Section 1 explains the use of this document. Section 2 lists reference documents. Section 3 allocates spacecraft resources, such as mass, power, and data rate, to the IMAGER instrument. Section 4 contains government-accepted operation constraints. Section 5 contains government-accepted deviations from the GIRD. Section 6 contains Design Verification Requirements. Section 7 contains a list of acronyms used within this document.

1.2 Requirements Terminology

The following requirements terminology is used throughout this document:

The term “shall” designates a requirement that must be achieved and is synonymous with the term “threshold.”

Page 2 of 16 Printed Wednesday, February 9, 2022

ID

GXIUIID13

GXIUIID14

GXIUIID15

GXIUIID16

GXIUIID17

GXIUIID18

GXIUIID19

GXIUIID20

GXIUIID21

GXIUIID22

GXIUIID23

Object Number

1.2.0-3

1.2.0-4

1.2.0-5

1.2.0-6

1.2.0-7

1.2.0-8

1.2.0-9

1.2.0-10

1.2.0-11

1.3

1.3.0-1

418-XO-GXIUIID-0023, RM Version, GeoXO Imager (GXI) Unique Instrument Interface Document (UIID)

The term “should” designates a desired level of performance the government would like the contractor to strive towards achieving and is synonymous with the term “goal.”

All other terms, including “will”, only designate statements of fact or intentions of the government and are not to be interpreted as contractor requirements.

The term “TBD” means, “to be determined.” This is applied to requirements or values that have not been defined. The contractor is responsible for proposing a requirement or value and its corresponding rationale for all TBD requirements.

TBD requirement proposals are to be made in coordination with the government and may involve other contractors.

The contractor should request approval from the government before proceeding with its proposed TBD requirement or value.

The term “TBR” means, “to be reviewed.” This is applied to requirements or values that are subject to review by the government and the contractor. The contractor should review and suggest a modified value and rationale for all TBR requirements.

The “TBR” provides an indication that the value may change upon review.

TBR requirement proposals will be made in coordination with the government and may involve other contractors.

The contractor should request approval from the government before proceeding with its proposed TBR requirement or value.

The term “TBS” means, “to be supplied.” The government will supply TBS requirements. The government will provide a date or milestone at which each TBS requirement will be supplied.

1.3 Order of Precedence

The order of precedence of interface requirements documents is the UIID at the highest level, followed in order by the GIRD, ICD, and Instrument Description Document (IDD).

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ID

GXIUIID24

GXIUIID25

Object Number

2.0-1

418-XO-GXIUIID-0023, RM Version, GeoXO Imager (GXI) Unique Instrument Interface Document (UIID)

2 Applicable Documents Reserve

Page 4 of 16 Printed Wednesday, February 9, 2022

ID

GXIUIID26

GXIUIID27

GXIUIID28

GXIUIID29

GXIUIID30

GXIUIID31

GXIUIID32

GXIUIID33

GXIUIID34

GXIUIID35

GXIUIID36

GXIUIID37

GXIUIID38

GXIUIID39

GXIUIID40

GXIUIID41

GXIUIID42

GXIUIID43

GXIUIID44

Object Number

3.0-1

3.1

3.1.1

3.1.1.0-1

3.1.2

3.1.2.0-1

3.1.3

3.1.3.0-1

3.1.4

3.1.4.0-1

3.2

3.2.1

3.2.1.0-1

3.2.2

3.2.2.0-1

3.2.3

3.2.3.0-1

3.2.4

418-XO-GXIUIID-0023, RM Version, GeoXO Imager (GXI) Unique Instrument Interface Document (UIID)

3 Allocations The GEO-XO provides communications, power and a platform for the IMAGER instrument. The following paragraphs allocate these resources to IMAGER.

3.1 Command and Data Handling

3.1.1 Instrument-to-Spacecraft Science Rate

The instrument science and engineering 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 150 million (106) bits per second (TBR) when averaged over any 5 second period. (CCR-X00011)

3.1.2 Telemetry Data Rate

Housekeeping telemetry data rate, including all overhead associated with CCSDS packetization by the instrument, at the spacecraft interface shall not exceed 1024 bits per second when averaged over any 5 second period.

3.1.3 Application Process Identifiers

The IMAGER shall use no more than 255 consecutive Application Process Identifiers (APIDs) for science, telemetry, and command packets.

3.1.4 GEO-XO Reliable Data Delivery Protocol Packet Rate

The IMAGER shall transmit to the spacecraft no more than 400 GRDDP Packets per second. (CCR-X00039A)

3.2 Power

3.2.1 Average Operational Power

The IMAGER shall draw operational average power, inclusive of heaters, of no more than 614 Watts from up to eight total feeds including primary and redundant feeds.

Operational average power is the total power into an instrument averaged over any 5 minute period. (CCR-X00011) (CCR-X00017) (CCR-X00039A)

3.2.2 Maximum Operational Power

The IMAGER shall draw operational maximum power of no more than 985 Watts.

Operational maximum power is the total power into an instrument averaged over any 20 ms period. (CCR-X00011) (CCR-X00017)

3.2.3 Average Survival Power

The IMAGER shall draw average survival power of no more than 400 Watts.

Average survival power is the total power into an instrument averaged over any 72 minute period. (CCR-X00017)

3.2.4 Maximum Survival Power

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ID

GXIUIID45

GXIUIID46

GXIUIID47

GXIUIID48

GXIUIID49

GXIUIID50

GXIUIID51

GXIUIID52

GXIUIID53

GXIUIID54

GXIUIID126

GXIUIID55

GXIUIID56

Object Number

3.2.4.0-1

3.3

3.3.0-1

3.3.1

3.3.1.0-1

3.3.2

3.3.2.0-1

3.3.2.0-2

3.3.3

3.3.3.0-1

3.3.3.0-2

3.3.4

3.3.4.0-1

418-XO-GXIUIID-0023, RM Version, GeoXO Imager (GXI) Unique Instrument Interface Document (UIID)

The IMAGER shall draw maximum survival power of no more than 600 Watts.

Maximum survival power is the total power into an instrument averaged over any 20 ms period. (CCR-X00017)

3.3 Mechanical

The requirements in this section apply to the structural and mechanical components of the instrument flight units (sensor unit, electronics unit and, if applicable, auxiliary electronics unit).

3.3.1 Mass Properties

The IMAGER, including all units and cabling between units, shall have mass less than 330 (TBR) kilograms.

3.3.2 Cabling Between Units

If there are external units mounted directly to the spacecraft, the IMAGER shall accommodate any cable length between the units up to but not exceeding the lengths of 4 meters.

Cables between IMAGER units will be the responsibility of the IMAGER contractor.

3.3.3 Volume

The IMAGER Sensor Unit operational (deployed) configurations, including mounts, thermal blankets and connectors, shall have dimensions that do not exceed the limits provided below.

Height: 1620 millimeters

Length: 1360 millimeters

Width: 1750 millimeters

(CCR-X00017)

The IMAGER Sensor Unit stowed configurations, including mounts, thermal blankets and connectors, shall have dimensions that do not exceed the limits provided below.

Height: 1500 millimeters

Length: 1200 millimeters

Width: 1750 millimeters

(CCR-X00017)

3.3.4 Optical Port Field-of-View

The spacecraft shall provide the sensor unit’s optical port a clear field-of-view within 65o of nadir as shown in the following figure.

Page 7 of 16 Printed Wednesday, February 9, 2022

ID

GXIUIID67

GXIUIID69

GXIUIID70

GXIUIID72

GXIUIID74

GXIUIID75

Object Number

3.4.1.0-1

3.4.2

3.4.2.0-1

3.4.2.0-2

3.4.3

3.4.3.0-1

418-XO-GXIUIID-0023, RM Version, GeoXO Imager (GXI) Unique Instrument Interface Document (UIID) the centroid of the sensor unit mounts.

Filtered Integrated Angular Momentum Limits Limit

Axis (N-m-s2) Roll 0.50 Pitch 0.35 Yaw 0.50

(CCR-X00017)

3.4.2 Angular Momentum Limits

The absolute value of the high pass filtered angular momentum produced by the sensor unit referenced at the satellite center of mass shall not exceed the values listed in the Angular Momentum Limits table. The high pass filter is a second order Butterworth filter with a -3 dB cutoff frequency at 0.01 Hz. The satellite center of mass will be within 2 meters of the centroid of the sensor unit mounts.

Angular Momentum Limits Limit

Axis (N-m-s) Roll 0.10 Pitch 0.05 Yaw 0.10

(CCR-X00017)

The absolute value of the band-pass-filtered instrument angular momentum in each orthogonal axis shall not exceed the values listed in the One-Sixth Octave Band Filtered Angular Momentum Limits table. The bandpass filters for this requirement are defined as a series of eighth-order Butterworth bandpass filters with -3 dB bandwidth of one sixth of an octave. The first filter in the series has its center frequency at 0.015625 Hz, and the center frequencies for the series are spaced at one-twelfth octave up to 10 Hz. The Bandpass-Filtered Angular Momentum Limits apply to filters with center frequency greater than f1 and less than or equal to f2.

One-Sixth Octave Band Filtered Angular Momentum Limits f1 (Hz) f2 (Hz)

Limit (N-m-s)

0.01 0.25 0.050

0.25 1.0 0.020

1.0 10.0 0.015

(CCR-X00039A)

3.4.3 Instrument Translation Acceleration Limits

The translational accelerations induced by the instrument sensor at each mount shall not exceed the limits specified in the Instrument-to-Spacecraft Linear Acceleration Limits table below. The accelerations are those induced by operation

Page 12 of 16 Printed Wednesday, February 9, 2022

ID

GXIUIID104

GXIUIID105

GXIUIID106

Object Number

4.0-1

4.0-2

418-XO-GXIUIID-0023, RM Version, GeoXO Imager (GXI) Unique Instrument Interface Document (UIID)

4 Constraints In order to ensure proper instrument performance or to prevent possible instrument damage, the following Government-approved constraints are imposed by the instrument developer on spacecraft integration and test activities, including launch, activation and operations.

No constraints have been identified at this time.

Page 13 of 16 Printed Wednesday, February 9, 2022

ID

GXIUIID107

GXIUIID108

Object Number

5.0-1

418-XO-GXIUIID-0023, RM Version, GeoXO Imager (GXI) Unique Instrument Interface Document (UIID)

5 GIRD Deviations This section identifies GIRD requirements that the Government has deviated from for this instrument. Where appropriate, corresponding GIRD paragraph titles and numbers are identified in parentheses.

Page 14 of 16 Printed Wednesday, February 9, 2022

ID

GXIUIID109

GXIUIID110

GXIUIID111

GXIUIID112

GXIUIID114

GXIUIID115

GXIUIID116

GXIUIID117

GXIUIID118

GXIUIID119

GXIUIID120

GXIUIID121

Object Number

6.0-1

6.1

6.1.0-1

6.1.0-2

6.2

6.2.0-1

6.2.0-2

6.2.0-3

6.2.0-4

6.2.0-5

6.2.0-6

418-XO-GXIUIID-0023, RM Version, GeoXO Imager (GXI) Unique Instrument Interface Document (UIID)

6 Design Verification Requirements The following requirements represents only a portion of the overall system verification ( i.e., contractor derived requirements are not described) that must be integrated into the total system program which verifies that the system will meet the mission requirements. A system performance verification program documenting the overall verification plan, implementation, and results is required which will provide traceability from mission specification requirements to launch and initial on-orbit capability. This will also provide the baseline for tracking on-orbit performance versus pre-launch capability.

6.1 Radiated Emissions, Electric Field (RE 102)

Radiated narrow band electric field levels generated by the instrument shall not exceed the levels specified in the Sensor Unit and Electronics Unit Notches Table below except for the DCS Receiver bands specified in GXIUIID121.

Radiated Emissions Notch Table

Frequency Range (MHz) Limits (dBuV/meter)

1164.45‐1188.45 5

1210.1‐1245.1 5

1560‐1595 5

2033.5‐2037.5 12

Note: When S/C Vendor selects GPS band to be used, other bands will be released.

The test procedure used for this test shall be in accordance with MIL-STD-461, RE102.

6.2 Radiated Emissions in DCS Receiver Bands

Radiated emission measurements in the DCS receiver bands shall be made in accordance with MIL-STD-461, RE102 with the EMI meter replaced by a spectrum analyzer preceded by a low noise pre-amplifier such that the test system noise figure is equal to or less than 3 dB, e.g., an HP-8566 spectrum analyzer preceded by a MITEQ AU-2A-0550 pre-amplifier or equivalent.

The spectrum analyzer levels and the difference in the levels shall be recorded for both white noise and spurious signals before and after power is applied to the instrument clock and control signals.

The test antenna shall be tuned to the center of the frequency band specified in DCS EMC Test Parameters Table (GXIUIID121).

Prior to making the actual measurements, the test antenna shall be de-mated and the cable terminated with 50 ohms for self calibration.

The noise floor of the measuring equipment shall be verified to be lower than the specified maximum signal level in a 100 Hz resolution bandwidth.

Radiated emission levels generated by the instrument shall not exceed the maximum signal levels specified in the DCS EMC Test Parameters Table below.

Page 15 of 16 Printed Wednesday, February 9, 2022

ID

GXIUIID121

Object Number

6.2.0-6

418-XO-GXIUIID-0023, RM Version, GeoXO Imager (GXI) Unique Instrument Interface Document (UIID)

Unit Name Designated Frequency

Band

Measurement Bandwidth (Hz)

Dwell Time (Seconds)

Minimum Measurement Time Analog Measurement

Receiver (sec/kHz)

Max. Field Intensity (dBuV/m)

Instrument Boxes

Within the S/C Bus

DCS 100 0.015 0.15 ‐8

(each box)

Imager Outside S/C

Bus

(GXI)

DCS 100 0.015 0.15 ‐24

Page 16 of 16 Printed Wednesday, February 9, 2022

ID

GXIUIID123

GXIUIID124

Object Number

7.0-1

418-XO-GXIUIID-0023, RM Version, GeoXO Imager (GXI) Unique Instrument Interface Document (UIID)

7 Acronyms APID Application Process Identifier

C&DH Command and Data Handling

CCSDS Consultative Committee for Space Data Systems

GIRD General Interface Requirements Document

GOES Geostationary Operational Environmental Satellite

GSFC Goddard Space Flight Center

GXI GEO‐XO Imager

Hz Hertz

ICD Interface Control Document

IDD Instrument Description Document kg kilogram m meter

Mbps million bits per second mg milli‐g’s (where g is gravitational acceleration at Earth surface)

NASA National Aeronautics and Space Administration

PORD Performance and Operational Requirements Document

SRS Shock Response Spectra

TBD to be determined

TBR to be resolved

TBS to be specified

UIID Unique Instrument Interface Document

Effective Date: May 13, 2021 418-XO-GXIUIID-0023 Expiration Date: Five years from date of last signature Version 2.1 Responsible Organization: GeoXO Flight Project/Code 418

Document Change Record (DCR)

CCR GEO-XO#: X00003 Rev: Title: GEO-XO – GXIUIID Document Baseline Contract # N/A GOES S/C: GeoXO Effectivity: Instruments CCB Status: Approved Doc #: 418-XO-GXIUIID-0023 CCB Date: 11/02/2020 Doc Version: 1.0 Contract Mod#: N/A DOORs Version: 1.0 Doc Change Date: Nov. 02, 2020 DOORs ID #: N/A

CCR GEO-XO#: X00011 Rev: Title: GXIUIID: Updates for Phase A Contract # N/A GOES S/C: GeoXO Effectivity: Instruments CCB Status: Approved Doc #: 418-XO-GXIUIID-0023 CCB Date: 04/20/2021 Doc Version: 1.1 Contract Mod#: N/A DOORs Version: 1.1 Doc Change Date: Apr. 20, 2020 DOORs ID #: Modify: GXIUIID30 (3.1.1.0-1), 39 (3.2.1.0-1), 41 (3.2.2.0-1), 58 (3.3.5), 75

(3.4.3.0-1), 77 (3.4.3.0-2), 95 (3.4.6.0-1), 97 (3.4.6.0-2) Add: GXIUIID125 (3.3.5.0-2)

CCR GEO-XO#: X00017 Rev: Title: GXIUIID: More updates for Phase A Contract # GXI- 80GSFC21C0061 GOES S/C: GeoXO Effectivity: Instruments

GXI - 80GSFC21C0062

CCB Status: Approved Doc #: 418-XO-GXIUIID-0023 CCB Date: 05/13/2021 Doc Version: 2.0 Contract Mod#: 1 DOORs Version: 2.0 Doc Change Date: May 13, 2021 DOORs ID #: Modify: GXIUIID39 (3.2.1.-1), 41 (3.2.2.0-1), 43 (3.2.3.0-1), 45 (3.2.4.0-1), 54 (3.3.3.0-1), 59 (3.3.5.0-1), 67 (3.4.1.0-1), 70 (3.4.2.0-1), 92 (3.4.5.0-1), 125 (3.3.5.0-2) Add: GXIUIID126 (3.3.3.0-2), 127 (3.4.5.0-2)

CM Note: GXI Instrument is awarded, contract numbers are added, and signature page is updated to version 2.0.

CCR GEO-XO#: X00039 Rev: A Title: GXIUIID: Midway update for Phase A Contract # GXI- 80GSFC21C0061 GOES S/C: GeoXO Effectivity: Instruments

GXI - 80GSFC21C0062

CCB Status: Approved Doc #: 418-XO-GXIUIID-0023 CCB Date: 01/18/2022 Doc Version: 2.1 Contract Mod#: P0006 DOORs Version: 2.1 Doc Change Date: Jan. 27, 2022 DOORs ID #: Modify: GXIUIID36 (3.1.4.0-1), 39 (3.2.1.0-1), 64 (3.4), 72 (3.4.2.0-3), 75

(3.4.3.0-1), 77 (3.4.3.0-3), 92 (3.4.5.0-1), 95 (3.4.6.0-1), 97 (3.4.6.0-3), 112 (6.1.0-1), 121 (6.2.0-6), 127 (3.4.5.0-2), 45 (3.2.4.0-1), 54 (3.3.3.0-1), 59 (3.3.5.0-1), 67 (3.4.1.0-1), 70 (3.4.2.0-1), 92 (3.4.5.0-1), 125 (3.3.5.0-2)

Add: GXIUIID128 (3.4.7), 132 (3.4.7.0-1), 129 (3.3.6), 130 (3.3.6.0-1), 131 (3.3.6.0-2)