Attachment D UIID.pdf

Effective Date: November 02, 2020 418-XO-GXIUIID-0023 Expiration Date: Five years from date of last signature Version 1.0 Responsible Organization: GEO-XO Flight Project/Code 418

Geostationary and eXtended Orbits (GEO-XO) Unique Instrument Interface Document (UIID)

Signature page

Prepared by:

Electronically approved 11/02/2020

Michael A. Shallcross Date GEO XO Flight Project, System Eng.

NASA GSFC, Code 418

Reviewed by:

Electronically approved 11/02/2020

Alexander Krimchansky Date GEO XO Flight Project, Sys. Eng. Mgr.

NASA GSFC, Code 599

Electronically approved 11/02/2020

Phillip Driggers Date GEO XO Flight Project, Sys. Eng. Mgr.

NASA GSFC, Code 599

Approved by:

Electronically approved 11/02/2020

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

/GEO-XO Imager

GXIUIID

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

Version: 1.0 Printed by: rkhoover Printed on: Monday, November 2, 2020

No filter applied.

No sort applied.

Generated from DOORS 9.6.1.11

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 5North Field-of-View

3.3.6 6Mounting

3.4 6Instrument-to-Spacecraft Disturbances

3.4.1 6Integrated Angular Momentum

3.4.2 6Angular Momentum Limits

3.4.3 7Instrument Translation Acceleration Limits

3.4.4 9Predicted Interface Force and Torque (PIFT) Responses

3.4.5 9Spacecraft Mounting Stiffness

3.4.6 10External Sourced Translation Acceleration Limits

3.5 11Thermal

3.6 11Instrument Purge Requirements

Project: GEO-XO Imager Module: GXIUIID Baseline Version: 1.0

Contents ii

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 Monday, November 2, 2020

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, GEO-XO 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 Monday, November 2, 2020

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, GEO-XO 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).

Page 3 of 16 Printed Monday, November 2, 2020

ID

GXIUIID24

GXIUIID25

Object Number

2.0-1

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

2 Applicable Documents Reserve

Page 4 of 16 Printed Monday, November 2, 2020

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, GEO-XO 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 130 million (106) bits per second (TBR) when averaged over any 5 second period.

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 300 GRDDP Packets per second.

3.2 Power

3.2.1 Average Operational Power

The IMAGER shall draw operational average power, inclusive of heaters, of no more than 400 Watts from up to four (TBR) total feeds. Operational average power is the total power into an instrument averaged over any 5 minute period.

3.2.2 Maximum Operational Power

The IMAGER shall draw operational maximum power of no more than 575 Watts from up to four (TBR) total feeds. Operational maximum power is the total power into an instrument averaged over any 20 ms period.

3.2.3 Average Survival Power

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

Average survival power is the total power into an instrument averaged over any 72 minute period.

3.2.4 Maximum Survival Power

Page 6 of 16 Printed Monday, November 2, 2020

ID

GXIUIID59

GXIUIID60

GXIUIID61

GXIUIID62

GXIUIID63

GXIUIID64

GXIUIID65

GXIUIID66

GXIUIID67

GXIUIID69

GXIUIID70

GXIUIID72

Object Number

3.3.5.0-1

3.3.6

3.3.6.0-1

3.3.6.0-2

3.3.6.0-3

3.4

3.4.0-1

3.4.1

3.4.1.0-1

3.4.2

3.4.2.0-1

3.4.2.0-2

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

The spacecraft shall provide the sensor unit’s radiator face a 2 steradian field-of-view to space excepting a field-of-view blockage with less than 50 W (TBR) back loading.

3.3.6 Mounting

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

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.

3.4 Instrument-to-Spacecraft Disturbances

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

3.4.1 Integrated Angular Momentum

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 satellite center of mass will be within 2 meters of the centroid of the sensor unit mounts.

Filtered Integrated Angular Momentum Limits

Axis Limit

(N-m-s2) Roll 0.462 Pitch 0.325 Yaw 0.484

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

Axis Limit

(N-m-s) Roll 0.09 Pitch 0.06 Yaw 0.10

The absolute value of the band pass filtered instrument 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

Page 7 of 16 Printed Monday, November 2, 2020

ID

GXIUIID72

GXIUIID74

Object Number

3.4.2.0-2

3.4.3

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

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

3.4.3 Instrument Translation Acceleration Limits

Page 8 of 16 Printed Monday, November 2, 2020

ID

GXIUIID75

GXIUIID77

Object Number

3.4.3.0-1

3.4.3.0-2

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

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 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.

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

The translational accelerations induced by the instrument sensor unit at each 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.

Page 9 of 16 Printed Monday, November 2, 2020

ID

GXIUIID77

GXIUIID79

GXIUIID80

GXIUIID81

GXIUIID82

GXIUIID83

GXIUIID84

GXIUIID85

GXIUIID86

GXIUIID87

GXIUIID88

GXIUIID89

GXIUIID90

GXIUIID91

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

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

Instrument to Spacecraft Linear Acceleration SRS Limits f (Hz)

SRS

Limit (mg)

SRS

Limit/

Q (mg) f (Hz)

SRS

Limit (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

3.4.4 Predicted Interface Force and Torque (PIFT) Responses

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

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

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

The IMAGER shall increment the future time values for predicted forces and torques sent to the spacecraft by 50 ms or less.

The IMAGER shall send to the spacecraft predicted forces and torques at least 250 ms prior to the predicted time.

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

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

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

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

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

3.4.5 Spacecraft Mounting Stiffness

Page 10 of 16 Printed Monday, November 2, 2020

ID

GXIUIID92

GXIUIID94

GXIUIID95

GXIUIID97

Object Number

3.4.5.0-1

3.4.6

3.4.6.0-1

3.4.6.0-2

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

Reserve.

3.4.6 External Sourced Translation Acceleration Limits

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.

External Source Translational Acceleration Limits for Spacecraft to Instrument Table f1

(Hz) f2

(Hz)

Peak

Limit

(mg) f1

(Hz) f2

(Hz)

Peak

Limit

(mg) f1

(Hz) f2

(Hz)

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

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

Page 11 of 16 Printed Monday, November 2, 2020

ID

GXIUIID97

GXIUIID99

GXIUIID100

GXIUIID101

GXIUIID102

GXIUIID103

Object Number

3.4.6.0-2

3.5

3.5.0-1

3.6

3.6.0-1

3.6.0-2

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

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

3.5 Thermal

The total heat transfer to the spacecraft of all instrument electronics units shall not exceed 220 Watts.

3.6 Instrument Purge Requirements

The spacecraft shall provide a continuous GN2 purge.

The spacecraft shall provide a continuous GN2 purge to the integrated IMAGER sensor module when not under vacuum via the t-0 purge system.

Page 12 of 16 Printed Monday, November 2, 2020

ID

GXIUIID104

GXIUIID105

GXIUIID106

Object Number

4.0-1

4.0-2

418-XO-GXIUIID-0023, RM Version, GEO-XO 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 Monday, November 2, 2020

ID

GXIUIID107

GXIUIID108

Object Number

5.0-1

418-XO-GXIUIID-0023, RM Version, GEO-XO 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 Monday, November 2, 2020

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, GEO-XO 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)

1560‐1595 (TBR) 10 (TBR)

1660‐1670 (TBR) 45 (TBR)

2022‐2038 (TBR) 11 (TBR)

7210‐7223 (TBR) 39 (TBR)

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.

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ID

GXIUIID121

Object Number

6.2.0-6

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

DCS EMC Test Parameters Table

Unit Name DCS Band (MHz)

Measurement Bandwidth

(Hz)

Dwell Time

(Seconds)

Minimum Measurement Time Analog Measurement

Receiver (sec/kHz)

Max.

Filed

Intensity (dBuV/m)

Instrument Electronics

Box

401.700 – 402.400

100 .015 0.15 10 (each box)

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ID

GXIUIID123

GXIUIID124

Object Number

7.0-1

418-XO-GXIUIID-0023, RM Version, GEO-XO 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: November 02, 2020 418-XO-GXIPORD-0024 Expiration Date: Five years from date of last signature Version 1.0 Responsible Organization: GEO-XO Flight Project/Code 418

Document Change Record (DCR)

CCR GEO-XO#: X00004 Rev: A Title: GEO-XO – GXIPORD Document Baseline Contract # N/A GOES S/C: GEO-XO Effectivity: Instrument CCB Status: Approved Doc #: 418-XO-GXIPORD-0024 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