Attachment E-6 -ABIUIID.pdf

Effective Date: May 3, 2004 417-R-ABIUIID-0010 Responsible Organization: GOES-R/Code 417 Baseline Version 2.30

Geostationary Operational Environmental Satellite (GOES)

GOES-R Series

Advanced Baseline Imager (ABI)

Unique Instrument Interface Document

(UIID)

February 27, 2020

National Aeronautics and Space Administration

Goddard Space Flight Center Greenbelt, Maryland

Effective Date: Date of Last Signature 417-R-ABIUIID-0010 Responsible Organization: GOES-R/Code 417

To verify the correct version of this document, please contact the GOES-R Series Configuration Management Office

/ABI

ABI UIID

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

Version: 2.30 Printed by: rkhoover Printed on: Wednesday, March 4, 2020

No filter applied.

No sort applied.

Generated from DOORS 9.6.1.11

Contents

1 1Scope

1.1 1Document Overview (CCR 00150)

1.2 1Missing Requirements

1.3 1Order 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 4GOES-R Reliable Data Delivery Protocol Packet Rate (CCR 01185)

3.2 4Power

3.2.1 4Average Power Operational (CCR 00251A)

3.2.2 4Maximum Operational Power (CCR 00251A)

3.2.3 4Peak Operational Current (CCR 00251A)

3.2.4 4Average Survival Power (CCR 00251)

3.2.5 5Maximum Survival Power

3.2.6 5Cryocooler Power (CCR 01049)

3.3 5Mechanical (CCR 00150)

3.3.1 5Mass Properties

3.3.2 5Cabling Between Units

3.3.3 6Volume

3.3.4 8Optical Port Field-of-View

3.3.5 8North Field-of-View

3.3.6 8East/West Field-of-View

3.3.7 10Reserved (CCR 00019)

3.3.8 10Mounting

3.4 10Instrument-to-Spacecraft Disturbances

3.4.1 10Integrated Angular Momentum (CCR 00162)

3.4.2 10Angular Momentum Limits (CCR 00162)

3.4.3 11Instrument Translation Acceleration Limits

3.4.4 13Predicted Interface Force and Torque (PIFT) Responses

3.4.5 13Spacecraft Mounting Stiffness (CCR 00162)

3.4.6 14External Sourced Translation Acceleration Limits (CCR 00162)

3.5 15Thermal

3.6 15Instrument Purge Requirements (CCR 01459)

Project: ABI Module: ABI UIID Baseline Version: 2.30

Contents ii

4 16Constraints

5 17GIRD Deviations

6 19Acronyms

Contents iii

Page 1 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID1

ABIUIID2

ABIUIID94

ABIUIID62

ABIUIID105

ABIUIID3

ABIUIID5

ABIUIID6

ABIUIID92

Object Number

1.0-1

1.0-2

1.0-3

1.1

1.1.0-1

1.2

1.2.0-1

1.3

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

1 Scope

The purpose of this Unique Instrument Interface Document (UIID) is two-fold. The first is to allocate GOES-R series spacecraft resources to the Advanced Baseline Imager (ABI). The second is to serve as a core building block on which the ABI-spacecraft interface can be designed. The spacecraft integrating contractor and the ABI 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 ABI and spacecraft contractors.

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

The ABI is a multispectral, two-axis scanning 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. ABI is designed to measure solar reflected radiance simultaneously in all spectral channels.

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 (CCR 00150)

Together, the General Interface Requirements Document (GIRD) and the ABI UIID establish the ABI-spacecraft interface requirements. The GIRD applies to all GOES-R instruments while the ABI UIID is specific to the ABI. 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 ABI instrument. Section 4 contains government-accepted operation constraints. Section 5 contains government-accepted deviations from the GIRD. Section 6 contains a list of acronyms used within this document. (CCR 00150)

1.2 Missing Requirements

The term “(TBD)”, which means “to be determined”, applied to a missing requirement means that the instrument contractor determines the missing requirement in coordination with the spacecraft contractor.

The term “(TBR)”, which means “to be refined/reviewed”, means that the requirement is subject to review for appropriateness by both contractors, and subject to revision. The instrument contractor is liable for compliance with the requirement as if the “TBR” notation did not exist. The “TBR” merely provides an indication that the value is more likely to change in a future modification than requirements not accompanied by a “TBR”.

1.3 Order of Precedence

Page 2 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID93

Object Number

1.3.0-1

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

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).

Page 3 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID9

ABIUIID98

Object Number

2.0-1

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

2 Applicable Documents

Reserve

Page 4 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID11

ABIUIID12

ABIUIID13

ABIUIID14

ABIUIID15

ABIUIID16

ABIUIID17

ABIUIID88

ABIUIID89

ABIUIID134

ABIUIID136

ABIUIID18

ABIUIID19

ABIUIID20

ABIUIID21

ABIUIID22

ABIUIID146

ABIUIID153

ABIUIID121

ABIUIID154

ABIUIID23

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

3.2.2.0-2

3.2.2.0-3

3.2.3

3.2.3.0-1

3.2.4

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

3 Allocations

The GOES-R provides communications, power and a platform for the ABI instrument. The following paragraphs allocate these resources to ABI.

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 66.6 million (106) bits per second when averaged over any 5 second period.

3.1.2 Telemetry Data Rate

Housekeeping telemetry data rate, including all overhead associated with CCSDS packitization 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 ABI shall use no more than 255 consecutive Application Process Identifiers (APIDs) for science, telemetry, and command packets.

3.1.4 GOES-R Reliable Data Delivery Protocol Packet Rate (CCR 01185)

The ABI shall transmit to the spacecraft no more than 300 GRDDP Packets (as defined in the GIRD933 [3.2.5.2.1.0-1]) per second. (CCR 01185)

3.2 Power

3.2.1 Average Power Operational (CCR 00251A)

The ABI shall draw operational average power (as defined in the GIRD1183 [3.2.3.2.1.0-1]) of no more than 614 watts from all feeds with no more than 358 watts from the 28V feeds and 256 watts from the 70V feeds. (CCR 00251A) (CCR 02231) (CCR 03482)

3.2.2 Maximum Operational Power (CCR 00251A)

The ABI Electronics Unit shall draw operational maximum power (as defined in the GIRD1183 [3.2.3.2.1.0-1]) of no more than 363 watts. (CCR 00251A) (CCR 02176)

The ABI Cryocooler Electronics Unit shall draw operational maximum power (as defined in the GIRD1183 [3.2.3.2.1.0-1]) of no more than 212 watts. (CCR 02176)

The ABI shall draw operational maximum power (as defined in the GIRD1183 [3.2.3.2.1.0-1]) from the 70V spacecraft feeds of no more than 270 watts. (CCR 03482)

3.2.3 Peak Operational Current (CCR 00251A)

The ABI shall draw peak current (as defined in the GIRD1183 [3.2.3.2.1.0-1]) of no more than 1.4 amps from each of the 70V feeds. (CCR 03482)

3.2.4 Average Survival Power (CCR 00251)

Page 5 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID24

ABIUIID123

ABIUIID124

ABIUIID127

ABIUIID128

ABIUIID129

ABIUIID130

ABIUIID131

ABIUIID132

ABIUIID133

ABIUIID161

ABIUIID160

ABIUIID107

ABIUIID25

ABIUIID27

ABIUIID28

ABIUIID79

ABIUIID80

Object Number

3.2.4.0-1

3.2.5

3.2.5.0-1

3.2.6

3.2.6.0-1

3.2.6.0-2

3.2.6.0-3

3.2.6.0-4

3.2.6.0-5

3.2.6.0-6

3.2.6.0-7

3.2.6.0-8

3.3

3.3.0-1

3.3.1

3.3.1.0-1

3.3.2

3.3.2.0-1

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

The ABI shall draw survival average power (as required in the GIRD1183 [3.2.3.2.1.0-1]) from the 70V spacecraft feeds of no more than 415 watts. (CCR 00251) (CCR 01785) (CCR 03482)

3.2.5 Maximum Survival Power

The ABI shall draw survival maximum power (as defined in the GIRD1183 [3.2.3.2.1.0-1]) from the 70V spacecraft feeds of no more than 795 watts. (CCR 00251) (CCR 03482)

3.2.6 Cryocooler Power (CCR 01049)

The Spacecraft shall provide separate (in addition to Electronics Unit) single fault tolerant operational power source to each of the two Cryocooler Electronics. (reference GIRD233 and GIRD

1200). (CCR 01049)

The Spacecraft shall power either one of the Cryocooler Electronics (Primary or Redundant) independent of the Electronics Unit operational power source configuration. (CCR 01049)

The spacecraft shall by command power either one or both (primary and redundant) Cryocoolers Electronics simultaneously. (CCR 01049)

The Spacecraft shall power the Electronics Unit before powering the Cryocooler Electronics. (CCR 01049)

The Spacecraft shall power down the Cryocooler Electronics before or at the same time the Electronics Unit is powered down. (CCR 01049)

ABI shall limit the Cryocooler Electronics undershoot to -3V following removal of power from the Cryocooler electronics at the interface. (CCR 01049)

The spacecraft shall provide the capability for autonomous closed-loop temperature based power switching of the spacecraft 70V feeds to the ABI radiator and liquid line heaters. (CCR 03482)

The ABI shall survive uninterrupted power supplied by the spacecraft on all of the 70V feeds. (CCR 03482)

3.3 Mechanical (CCR 00150)

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).

(CCR 00150)

3.3.1 Mass Properties

The ABI, including all units and cabling between units, shall have mass less than 330.3 kilograms.

(CCR 00153) (CCR 00298) (CCR 02032)

3.3.2 Cabling Between Units

If there are external units mounted directly to the spacecraft, the ABI shall accommodate any cable length between the units up to but not exceeding the lengths defined in the following table:

Page 6 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID80

ABIUIID81

ABIUIID144

ABIUIID29

ABIUIID30

ABIUIID110

Object Number

3.3.2.0-1

3.3.2.0-2

3.3.2.0-3

3.3.3

3.3.3.0-1

3.3.3.0-2

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

Item Unit Cable Connections Length (m)

1 Electronics to Sensor 4

2 Cryocooler Electronics 1 to Sensor 4

3 Cryocooler Electronics 2 to Sensor 4

4 Cryocooler Electronics 1 to Electronics 1.5

5 Cryocooler Electronics 2 to Electronics 1.5

(CCR 00303)

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

The Cryocooler Electronics to Sensor Unit cables shall consist of two sections, with the length and connector type of each section to be negotiated and documented in the ABI to Spacecraft ICD.

(CCR 02053A)

3.3.3 Volume

The ABI Electronics Unit, including mounts, thermal blankets and connectors for both stowed and operational configurations, shall have dimensions that do not exceed the limits listed in the Electronics Unit Envelopes Table. (CCR 00124)

Electronics Unit Envelopes Table

Component Width (cm)

(X)

Height (cm)

(Y)

Depth (cm)

(Z)

Primary Electronics 40.0 40.0 65.0

Cryocooler Elec 1 25.0 20.0 25.0

Cryocooler Elec 2 25.0 20.0 25.0

(CCR 00303) (CCR 00124)

The ABI Sensor Unit stowed configuration, including mounts, thermal blankets and connectors, shall have dimensions that do not exceed the limits as shown in the ABI Sensor Unit Stowed Envelope Figure.

Page 9 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID96

Object Number

3.3.6.0-1

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

Linear dimensions are in millimeters.

ABI Sensor Unit Solar Calibration Fields of View Figure

Page 10 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID96

ABIUIID99

ABIUIID100

ABIUIID101

ABIUIID102

ABIUIID35

ABIUIID36

ABIUIID83

ABIUIID84

ABIUIID85

ABIUIID147

ABIUIID148

ABIUIID37

ABIUIID38

ABIUIID39

ABIUIID40

ABIUIID41

ABIUIID42

Object Number

3.3.6.0-1

3.3.7

3.3.7.0-1

3.3.7.0-2

3.3.7.0-3

3.3.8

3.3.8.0-1

3.3.8.0-2

3.3.8.0-3

3.3.8.0-4

3.3.8.0-5

3.3.8.0-6

3.4

3.4.0-1

3.4.1

3.4.1.0-1

3.4.2

3.4.2.0-1

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

(CCR 01063)

3.3.7 Reserved (CCR 00019)

Reserved (CCR 00019)

Reserved (CCR 00019)

Reserved (CCR 00019)

3.3.8 Mounting

The spacecraft shall provide the instrument sensor unit a nadir-facing mounting surface.

The spacecraft mounting surface shall have as a minimum the same dimensions of the sensor unit envelope anti-nadir plane.

The sensor unit mechanical interface shall lie within the anti-nadir plane of the sensor unit envelope.

The instrument sensor unit shall use kinematic mounts for its mechanical interface to the spacecraft.

The ABI Electronics Unit mounting surface shall be flat to less than 0.381 mm overall and less than

0.254 mm over any 25 mm by 25 mm square section. (CCR 02238)

The ABI Cryocooler Electronics Unit mounting surface shall be flat to less than 0.254 mm overall and less than 0.1 mm over the 25 mm by 25 mm square section centered around the mounting holes.

(CCR 02238)

3.4 Instrument-to-Spacecraft Disturbances

These requirements apply while the instrument is in orbit and operating.

3.4.1 Integrated Angular Momentum (CCR 00162)

The absolute value of the high pass filtered angular momentum integrated with respect to time shall not exceed the values listed in Filtered Integrated Angular Momentum Limits table. The filter is a second order Butterworth filter with a -3 dB cutoff frequency at 0.01 Hz. The spacecraft center of mass will be within 2 meters of the centroid of the sensor unit mounts. (CCR 00162) (CCR 02305

(RDW ABI-0084))

Filtered Integrated Angular Momentum Limits

Axis Limit

(N-m-s2) Roll 0.462 Pitch 0 325 Yaw 0.484

(CCR 00162)

3.4.2 Angular Momentum Limits (CCR 00162)

The absolute value of the high pass filtered angular momentum produced by the sensor unit referenced at the spacecraft 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

Page 11 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID42

ABIUIID112

ABIUIID113

ABIUIID43

Object Number

3.4.2.0-1

3.4.2.0-2

3.4.2.0-3

3.4.3

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID) cutoff frequency at 0.01 Hz. The spacecraft center of mass will be within 2 meters of the centroid of the sensor unit mounts. (CCR 00162) (CCR 02305 (RDW ABI-0084))

Angular Momentum Limits

Axis

Limit (N-m-s)

Roll 0.09 Pitch 0.06 Yaw 0.10

(CCR 00162) (CCR 00242)

The absolute value of the band pass filtered angular momentum shall not exceed the values listed in the One-Sixth Octave Band Filtered Angular Momentum Limits table. The table limits apply for each orthogonal axis. The band pass filters for the angular momentum are defined as a series of Butterworth band pass filters with -3 dB cutoff frequencies separated by one sixth of an octave, with a fourth order roll off and with a center frequency one-twelfth octave between the cutoff frequencies. The Filtered Angular Momentum Limits apply when the center frequency for the filter is greater than f1 and less than or equal to f2. The series of filters starts with a center frequency at

0.015625 Hz, and the center frequency is stepped by one-twelfth octave increments. (CCR 00162)

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 00162)

The absolute value of the narrow band filtered angular momentum shall not exceed the values listed in the Narrow Band Filtered Angular Momentum Limits table. The table limits apply for each orthogonal axis. The narrow band filters for the interface forces are defined as a series of filters with the following Laplace domain transfer function.

cc ss s with cc f 2

Where the term, s, is the subsidiary variable of the unilateral Laplace transformation; fc is the filter center frequency; and is equal to one percent. The center frequency for the series of filters is stepped by one-150th octave increments. The momentum limit applies when the center frequency for the filter is greater than f1 and less than or equal to f2. (CCR 00162)

Narrow Band Filtered Angular Momentum Limits f1 (Hz) f2 (Hz)

Limit (N-m-s)

0.01 0.2 0.020

0.2 1.0 0.015

1.0 10.0 0.010

(CCR 00162)

3.4.3 Instrument Translation Acceleration Limits

Page 12 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID44

ABIUIID103

Object Number

3.4.3.0-1

3.4.3.0-2

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

The translational accelerations at each instrument sensor unit mount shall not exceed the limits specified in the Instrument-to-Spacecraft Linear Acceleration Limits table below. The accelerations are those induced by operation of the sensor unit while mounted to a flexible interface. The limits apply to each orthogonal axis after the acceleration is filtered using at least a fourth-order band pass Butterworth filter with -3dB frequencies at f1 and f2 and with a fourth order roll off. Note that the filter has a fourth-order roll-off on both sides of the response. (CCR 00162) (CCR 02305 (RDW

ABI-0084))

Instrument-to-Spacecraft Space Linear Acceleration Limits f1

(Hz) f1

(Hz)

Peak Limit (mg) f1

(Hz) f1

(Hz)

Peak Limit (mg) f1

(Hz) f1

(Hz)

Peak Limit (mg)

0.0 512.0 8.80 26.9 30.2 0.16 114.0 128.0 1.30

0.9 10.1 0.60 28.5 32.0 0.16 120.8 135.6 1.30

6.3 32.0 0.40 30.2 33.9 0.56 128.0 143.7 1.30

20.2 101.6 2.20 32.0 35.9 0.56 135.6 152.2 0.56

64.0 322.5 5.50 33.9 38.1 0.56 143.7 161.3 0.56

203.2 512.0 6.60 35.9 40.3 0.56 152.2 170.9 0.56

9.0 10.1 0.16 38.1 42.7 0.56 161.3 181.0 1.70

9.5 10.7 0.16 40.3 45.3 0.56 170.9 191.8 1.70

10.1 11.3 0.16 42.7 47.9 0.56 181.0 203.2 1.70

10.7 12.0 0.16 45.3 50.8 0.56 191.8 215.3 1.70

11.3 12.7 0.16 47.9 53.8 0.56 203.2 228.1 1.40

12.0 13.5 0.16 50.8 57.0 1.80 215.3 241.6 1.40

12.7 14.3 0.16 53.8 60.4 1.80 228.1 256.0 1.40

13.5 15.1 0.16 57.0 64.0 1.80 241.6 271.2 1.40

14.3 16.0 0.16 60.4 67.8 1.80 256.0 287.4 1.40

15.1 17.0 0.16 64.0 71.8 1.80 271.2 304.4 1.40

16.0 18.0 0.16 67.8 76.1 1.80 287.4 322.5 1.40

17.0 19.0 0.16 71.8 80.6 0.56 304.4 341.7 1.40

18.0 20.2 0.16 76.1 85.4 0.56 322.5 362.0 1.40

19.0 21.4 0.16 80.6 90.5 0.56 341.7 383.6 1.40

20.2 22.6 0.16 85.4 95.9 0.56 362.0 406.4 1.40

21.4 24.0 0.16 90.5 101.6 0.56 383.6 430.5 1.40

22.6 25.4 0.16 95.9 107.6 0.56 406.4 456.1 1.40

24.0 26.9 0.16 101.6 114.0 0.56 430.5 483.3 1.40

25.4 28.5 0.16 107.6 120.8 1.30 456.1 512.0 1.40

(CCR 00162)

The translational accelerations at each instrument sensor unit mount shall produce an absolute peak acceleration Shock Response Spectra (SRS) less than the limits set in the Instrument to Spacecraft Linear Acceleration SRS Limits Table below. The limits apply to each orthogonal axis when using a quality factor, Q, of 50. The SRS is computed after the translational accelerations are high pass filtered with a fourth order Butterworth with a -3dB cut off at 1.0Hz. Use a logarithmic interpolation for both frequency and acceleration terms in the Instrument to Spacecraft Acceleration SRS Limits Table. (CCR 00162) (CCR 02305 (RDW ABI-0084))

Page 13 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID103

ABIUIID63

ABIUIID71

ABIUIID66

ABIUIID68

ABIUIID69

ABIUIID70

ABIUIID72

ABIUIID73

ABIUIID74

ABIUIID75

ABIUIID76

ABIUIID77

ABIUIID114

Object Number

3.4.3.0-2

3.4.4

3.4.4.0-1

3.4.4.0-2

3.4.4.0-3

3.4.4.0-4

3.4.4.0-5

3.4.4.0-6

3.4.4.0-7

3.4.4.0-8

3.4.4.0-9

3.4.4.0-10

3.4.4.0-11

3.4.5

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

Instrument to Spacecraft Linear Acceleration SRS Limits f

(Hz)

SRS

(mg)

SRS

Limit/

Q (mg) f

SRS

(mg)

SRS

Limit/

Q (mg)

10 4.0 0.08 138 18.0 0.36 30 4.0 0.08 165 18.0 0.36 30 12.0 0.24 177 82.0 1.64 52 12.0 0.24 198 82.0 1.64 59 80.0 1.60 210 18.0 0.36 66 80.0 1.60 225 18.0 0.36 73 12.0 0.24 236 59.0 1.18 90 12.0 0.24 264 59.0 1.18 90 18.0 0.36 275 18.0 0.36

112 18.0 0.36 285 18.0 0.36 118 58.0 1.16 295 45.0 0.90 132 58.0 1.16 300 45.0 0.90

(CCR 00162)

3.4.4 Predicted Interface Force and Torque (PIFT) Responses

The ABI shall send predicted forces, torques and future times to the spacecraft in a CCSDS source packet per the Command and Data Handling section of the GIRD.

The ABI shall send to the spacecraft predicted forces and torques resulting from normal instrument operations.

The ABI shall send to the spacecraft predicted forces and torques computed in the instrument coordinate system.

The ABI shall send to the spacecraft forces and torques predicted from a uniformly spaced series of future times.

The ABI shall increment the future time values for predicted forces and torques sent to the spacecraft by 50 ms or less. (CCR 01459)

The ABI shall send to the spacecraft predicted forces and torques at least 250 ms prior to the predicted time. (CCR 01459)

The ABI shall send to the spacecraft predicted forces and torques with the future time data using the P-field format in GIRD453.

The ABI shall send to the spacecraft predicted force data with a minimum resolution of 0.001 N.

(CCR 01459)

The ABI shall send to the spacecraft predicted torque data with a minimum resolution of 0.001 N-

m. (CCR 01459)

The ABI shall send to the spacecraft predicted force data with an accuracy of +/- 0.03 N. (CCR

01459) (CCR 02609 (RDW ABI-0125))

The ABI shall send to the spacecraft predicted torque data with an accuracy of +/- 0.03 N-m. (CCR

01459) (CCR 02609 (RDW ABI-0125))

3.4.5 Spacecraft Mounting Stiffness (CCR 00162)

Page 14 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID115

ABIUIID116

ABIUIID117

ABIUIID118

Object Number

3.4.5.0-1

3.4.5.0-2

3.4.6

3.4.6.0-1

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

The instrument shall meet its performance requirements while the sensor unit is mounted to a rigid plate supported at three flexible points with a first mode of 3.8 0.5 Hz and with the 6th mode less 12 Hz. (CCR 00162) (CCR 02039D)

The instrument shall meet its performance requirements when the diagonal modal viscous damping factors associated with the three flexible points are 15.0%. (CCR 00162) (CCR 02039D)

3.4.6 External Sourced Translation Acceleration Limits (CCR 00162)

The translational accelerations responses from sources external to the instrument sensor unit at the spacecraft side of each instrument sensor unit mount shall not exceed the limits specified in the External Source Translational Acceleration Limits for Spacecraft to Instrument Table below. The limits apply to each orthogonal axis after the acceleration is filtered using at least a fourth-order band pass Butterworth filter with -3dB frequencies at f1 and f2 and with a fourth order roll off.

Note that the filter has a fourth-order roll-off on both sides of the response. (CCR 00162)

External Source Translational Acceleration Limits for Spacecraft to Instrument Table f1 f2

Peak

Peak

Peak

Limit

(mg)

0.0 512.0 6.71 26.9 30.2 0.18 114.0 128.0 0.63

0.9 10.1 0.67 28.5 32.0 0.18 120.8 135.6 0.63

6.3 32.0 0.45 30.2 33.9 0.63 128.0 143.7 0.63

20.2 101.6 1.34 32.0 35.9 0.63 135.6 152.2 0.63

64.0 322.5 3.13 33.9 38.1 0.63 143.7 161.3 0.63

203.2 512.0 6.26 35.9 40.3 0.63 152.2 170.9 0.63

9.0 10.1 0.18 38.1 42.7 0.63 161.3 181.0 0.63

9.5 10.7 0.18 40.3 45.3 0.63 170.9 191.8 0.63

10.1 11.3 0.18 42.7 47.9 0.63 181.0 203.2 0.63

10.7 12.0 0.18 45.3 50.8 0.63 191.8 215.3 0.63

11.3 12.7 0.18 47.9 53.8 0.63 203.2 228.1 0.63

12.0 13.5 0.18 50.8 57.0 0.63 215.3 241.6 0.63

12.7 14.3 0.18 53.8 60.4 0.63 228.1 256.0 1.00

13.5 15.1 0.18 57.0 64.0 0.63 241.6 271.2 1.00

14.3 16.0 0.18 60.4 67.8 0.63 256.0 287.4 1.00

15.1 17.0 0.18 64.0 71.8 0.63 271.2 304.4 1.00

16.0 18.0 0.18 67.8 76.1 0.63 287.4 322.5 1.00

17.0 19.0 0.18 71.8 80.6 0.63 304.4 341.7 1.00

18.0 20.2 0.18 76.1 85.4 0.63 322.5 362.0 1.00

19.0 21.4 0.18 80.6 90.5 0.63 341.7 383.6 1.00

20.2 22.6 0.18 85.4 95.9 0.63 362.0 406.4 1.00

21.4 24.0 0.18 90.5 101.6 0.47 383.6 430.5 0.63

22.6 25.4 0.18 95.9 107.6 0.47 406.4 456.1 0.63

24.0 26.9 0.18 101.6 114.0 0.47 430.5 483.3 0.63

25.4 28.5 0.18 107.6 120 8 0.63 456.1 512.0 0.63

(CCR 00162) (CCR 02039D)

Page 15 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID119

ABIUIID90

ABIUIID91

ABIUIID120

ABIUIID143

ABIUIID142

ABIUIID141

Object Number

3.4.6.0-2

3.5

3.5.0-1

3.5.0-2

3.6

3.6-1

3.6-2

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

The translational acceleration responses from sources external to the instrument sensor unit at the spacecraft side of each instrument sensor unit mount shall produce an absolute peak acceleration Shock Response Spectra (SRS) less than the limits set in the External Source On Orbit Operational SRS Acceleration Limits Table below. The limits apply to each orthogonal axis for SRS natural frequencies when using a quality factor, Q, of 50. The SRS is computed after the acceleration is high pass filtered with a fourth order Butterworth filter with a -3dB cut off at 1.0 Hz. Use a logarithmic interpolation for both frequency and acceleration terms in the External Source On Orbit Operational SRS Acceleration Limits Table. (CCR 00162)

External Source On Orbit Operational SRS Accelerations Limits Tables

F (Hz)

SRS

Limit (mg)

SRS

Limit/ Q

(mg)

4.47 4.50 6.50 6.50 17.50 17.50 13.50 13.50 15.00 15.0 20.12 20.0 40.0 40.0

0.09 0.09 0.13 0.13 0.35 0.35 0.27 0.27 0.30 0.30 0.40 0.40 0.80 0.80

CCR 00162) (CCR 02039D)

3.5 Thermal

The instrument electronics unit total heat transfer to the spacecraft shall not exceed 120 Watts.

(CCR 00303) (CCR 02188)

The instrument cryocooler electronics units total heat transfer to the spacecraft shall not exceed 50 Watts each. (CCR 00303) (CCR 02188)

3.6 Instrument Purge Requirements (CCR 01459)

The spacecraft shall provide a continuous GN2 purge compliant to Spacecraft to ABI ICD requirements. (CCR 01459) (CCR 02130)

The spacecraft shall provide a continuous GN2 purge to the integrated ABI sensor module when not under vacuum via the t-0 purge system. (CCR 01459) (CCR 02130)

Page 16 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID55

ABIUIID56

Object Number

4.0-1

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) 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 18 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID152

ABIUIID158

ABIUIID156

ABIUIID157

ABIUIID159

ABIUIID155

Object Number

5.0-9

5.0-10

5.0-11

5.0-12

5.0-13

5.0-14

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

GIRD201 and GIRD844 are subject to the ABI FM1, FM2, FM3 and FM4 sensor units, GOES spacecraft mounting interface operational temperature limits deviation/waiver VR1-16-0511-1.

(CCR 03142 (RDW VR1-16-0511-1)) (CCR 03358 (RDW VR1-16-0511-2))

GIRD217 [3.2.2.5.0-1], GIRD 1180 [3.2.3.1.0-9], and GIRD1200 [3.2.3.2.3.1.0-2] are not applicable to ABI. (CCR 03482)

GIRD356 [3.2.3.2.2.1.1.0-4] is replaced with:

The spacecraft shall supply a steady-state dc source voltage of 69.2 Vdc to 70.8 Vdc for the instrument 70 Vdc power input connectors. (CCR 03482)

GIRD357 [3.2.3.2.2.1.1.0-5]] is replaced with:

The instrument shall operate the instrument survival heaters and associated passive control circuitry to maintain minimum turn-on temperatures with a steady-state dc source voltage of 69.2 Vdc to 70.8 Vdc for the instrument 70 Vdc power input connectors. (CCR 03482)

GIRD346 [3.2.3.2.3.4.0-1] is replaced with:

The spacecraft shall supply single fault tolerant survival heater power distribution to the ABI for the 70V feeds A1, A2, A3, B1, B2, and B3. (CCR 03482)

GIRD470 [3.2.5.9.2.0-1] is superseded by:

The spacecraft shall provide up to 21 analog signals per side to monitor critical temperature points to the ABI. (CCR 03482)

Page 19 of 19 Printed Wednesday, March 4, 2020

ID

ABIUIID59

ABIUIID60

Object Number

6.0-1

417-R-ABIUIID-0010, RM Version, Advanced Baseline Imager (ABI) Unique Instrument Interface Document (UIID)

6 Acronyms

ABI Advanced Baseline Imager 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 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