Following is the CDA version of XC02, last updated 10/31/95. CDA comments have not yet been incorporated.
AXAF
Advanced X-Ray
Astrophysics Facility
X-ray
Calibration
Test
GSE
Requirements
Document
CDR Internal Draft-09/29/95 9:54:24 AM
Prepared by
J.W. Arenberg
TRW
AXAF Telescope Project
1 1 SCOPE 1
2 APPLICABLE DOCUMENTS 2
2.1 REQUIRED DOCUMENTS 2
2.1.1 Team Member Documents 2
2.1.2 Government Specifications 3
3 REQUIREMENTS 4
3.1 COORDINATE SYSTEM 4
3.1.1 XRCF 4
3.1.2 Architectural Coordinate System 4
3.1.3 MDS 4
3.1.4 ATA 4
3.1.5 SCIENCE INSTRUMENT MODULE FIVE AXIS
MOUNT 4
3.1.6 HRMA 5
3.1.7 HRMA X-ray Detection System 5
3.2 UNITS 6
3.2.1 Length 6
3.3 TIME DESIGNATION 7
3.4 SUBSYSTEM REQUIREMENTS 8
3.4.1 MSFC Subsystems 8
3.4.1.1 X-ray Calibration Facility 8
3.4.1.2 X-ray Source System 8
3.4.1.2.1 Source Location 8
3.4.1.2.2 Knowledge of Source Location 8
3.4.1.3 X-ray Monochrometer 8
3.4.1.4 Motion Detection System 8
3.4.1.5 Autocollimating Telescope Assembly8
3.4.1.6 Master Control Computer 8
3.4.2 TRW Subsystems 9
3.4.2.1 Command Telemetry Unit Emulator 9
3.4.2.1.1Functional Purpose 9
3.4.2.1.2 Timing Signals 9
3.4.2.1.2.1 Frame Synchronization 9
3.4.2.1.2.2 FPSI Clock 9
3.4.2.1.2.3 CTUE Clock Stability 9
3.4.2.1.2.4 Facility Time Stamp 9
3.4.2.1.3 Data Formats 9
3.4.2.1.3.1 Number of Formats 9
3.4.2.1.3.2 Display of Format in Use9
3.4.2.1.3.3 Dissemination of Data 9
3.4.2.1.3.4 Data to the Master
Control Computer 9
3.4.2.1.3.5 Data to the SI/SIM EGSE10
3.4.2.1.4 Network Interface 10
3.4.2.1.5 Interface Protocol 10
3.4.2.1.6 Cross Commands 10
3.4.2.1.6.1 Veto of Cross Commands 10
3.4.2.1.6.2 Cross Command Alarm 10
3.4.2.1.6.3 Command Inhibit on
Detection of Cross Command 10
3.4.2.1.6.4 Manual Restart on Cross
Command 10
3.4.2.1.7 CTUE Security 10
3.4.2.1.7.1 Password Access 10
3.4.2.1.7.2 Command Acceptance 10
3.4.2.1.8 Proximity to RCTUs 10
3.4.3 EKC Subsystems 12
3.4.3.1 HRMA Support Structure 12
3.4.3.1.1 Weight 12
3.4.3.1.2 Decentration and Initial
Alignment Tilt Tolerance 12
3.4.3.1.3 Remote Tilt Capability 12
3.4.3.1.3.1 Remote Tilt Range-Pitch12
3.4.3.1.3.2 Remote Tilt Range-Yaw 12
3.4.3.1.3.3 Remote Tilt Accuracy 12
3.4.3.1.3.4 Remote Tilt Step Size 12
3.4.3.1.3.5 Repeatability of Motion12
3.4.3.1.3.5.1 Tip/Tilt 12
3.4.3.1.3.5.2 Despace 13
3.4.3.1.3.5.3 Decenter 13
3.4.3.1.3.5.4 Clocking 13
3.4.3.1.4 Rotation Angle Axis Location13
3.4.3.1.5 Orientation Reporting 13
3.4.3.1.6 Repositioning Rate 13
3.4.3.1.7 Stability 13
3.4.3.1.7.1 Thermal Stability 13
3.4.3.1.7.1.1 Transverse Stability 13
3.4.3.1.7.1.2 Axial Stability 14
3.4.3.1.7.2 Vibration Induced Motion14
3.4.3.1.7.2.1 Transverse Stability 14
3.4.3.1.7.2.2 Axial Stability 14
3.4.3.2 HRMA Forward Contamination Cover 14
3.4.3.2.1 Obscuration of X-ray Beam 14
3.4.3.2.2 Time to Open 14
3.4.3.3 HRMA Aft Contamination Cover 14
3.4.3.3.1 Obscuration of X-ray Beam 14
3.4.3.3.2 Time to Open 15
3.4.3.4 Purge Capability 15
3.4.3.5 OTG Mount 15
3.4.3.5.1 OTG Position Requirements 15
3.4.3.5.2 OTGs in Use 15
3.4.3.5.3 Obscuration of X-ray Beam by
Retracted OTG 15
3.4.3.5.4 OTG Alignment Tolerances 15
3.4.3.5.4.1 OTG Stability Tolerances15
3.4.3.5.4.2 OTG Repeatability
Tolerances 16
3.4.3.5.5 Insertion/Retraction Time 16
3.4.3.5.6 Position Feedback 16
3.4.3.5.7 OTG Insertion/Retraction Speed
and Acceleration 16
3.4.3.6 Movement of the Aft Contamination
Cover and OTGs 16
3.4.3.7 HRMA Shutter Assembly 17
3.4.3.7.1 Shutter Blade Clocking 17
3.4.3.7.2 Shutter Blade Designation 17
3.4.3.7.3 Simultaneity of Shutter
Operation 17
3.4.3.7.4 Remote Operation 17
3.4.3.7.5 Time to Reconfigure 17
3.4.3.7.6 Obscuration of x-ray beam 17
3.4.3.7.7 Shutter Opacity 18
3.4.3.7.8 Position Feedback 18
3.4.3.8 1-g Offloader 18
3.4.4 SAO Subsystems 19
3.4.4.1 HRMA X-ray Detector System 19
3.4.4.1.1 Image Plane Detectors 19
3.4.4.1.2 Beam Normalization Detectors19
3.4.4.1.2.1 BND-500 19
3.4.4.1.2.2 BND-H 19
3.4.5.1 Five Axis Mount 20
3.4.5.2 Physical Requirements 20
3.4.5.3 Envelope 20
3.4.5.4 Weight 20
3.4.5.5 Load Test 20
3.4.5.6 Failures 20
3.4.5.7 MDS Source Accommodation 20
3.4.5.7.1 Location of Source 20
3.4.5.7.2 Source Interface Location
Stability Relative to SI Aim Point 21
3.4.5.8 External Thermal Interface 21
3.4.5.9 Internal Thermal Interface 21
3.4.5.10 Operating Modes 21
3.4.5.11 Static Mode 21
3.4.5.12 Motion 21
3.4.5.12.1 X-axis: Range 21
3.4.6 Initial Alignment to Facility Optical
Axis 21
3.4.6.1 Initial Alignment in X 22
3.4.6.2 Initial Lateral Alignment 22
3.4.6.3 Initial Alignment of Normal to SIM
Focal Plane 22
3.4.6.4 Initial Rotation about FOA 22
3.4.6.5 X-axis: Mechanism Resolution 22
3.4.6.6 X-axis: Position Sensor Resolution22
3.4.6.7 X-axis: Rate 22
3.4.6.8 Y-axis: Range 22
3.4.6.9 Y-axis: Step Size 22
3.4.6.10 Y-axis: Resolution 22
3.4.6.11 Y-axis: Rate 22
3.4.6.12 Z-axis: Range 23
3.4.6.13 Z-axis: Step Size 23
3.4.6.14 Z-axis: Resolution 23
3.4.6.15 Z-axis: Rate 23
3.4.6.16 Dither Mode 23
3.4.6.16.1 Step Size 23
3.4.6.16.2 Range of Capability 23
3.4.6.16.3 Positonal Accuracy-
Absolute 23
3.4.6.16.4 Postional Accuracy-
Relative to Starting Position 23
3.4.6.16.5 24
3.4.6.16.6 Motion Control 24
3.4.6.16.7 Data 24
3.4.6.16.7.1 Data Display 24
3.4.6.16.7.2 Data Transmission 24
3.4.7 Stability 25
3.4.7.1 Thermal Stability 25
3.4.7.1.1 Transverse Stability 25
3.4.7.1.2 Axial Stability 25
3.4.7.2 Vibration Induced Motion 25
3.4.7.2.1 Transverse Stability 25
3.4.7.2.2 Axial Stability 25
3.4.8Rotation 25
3.4.8.1 X-axis: Rotation 25
3.4.8.2 Y-axis: Range 26
3.4.8.3 Y-axis: Step Size 26
3.4.8.4 Y-axis: Resolution 26
3.4.8.5 Y-axis: Rate 26
3.4.8.6 Z-axis: Range 26
3.4.8.7 Z-axis: Step Size 26
3.4.8.8 Z-axis: Resolution 26
3.4.9 FAM Controller Software 26
3.4.9.1 Communication 26
3.4.9.2 Data Recording 26
3.4.10 ACIS Cryogenic Interface 26
3.4.11 Access 27
3.4.12 Vacuum Interface 27
3.4.13 HRC Subsystems 28
3.4.13.1 Electrical Ground Support Equipment-
HRC 28
3.4.13.1.1 Command Validation 28
3.4.13.1.2 Telemetry Decommutation28
3.4.13.2 Verification 28
3.4.13.3 Command Format 28
3.4.13.4 SI Command Log 28
3.4.14 ACIS Subsystems 29
3.4.14.1 Electrical Ground Support Equipment-
ACIS 29
3.4.14.1.1 Command Validation 29
3.4.14.1.2 Telemetry Decommutation29
3.4.14.2 Verification 29
3.4.14.3 Command Format 29
3.4.14.4 SI Command Log 29
3.4.15 LETG Subsystems 30
3.4.16 HETG Subsystems 31
3.4.17 ASC Subsystems 32
3.4.18 Other Systems 33
3.4.18.1 X-ray Rehearsal Optic 33
3.4.18.1.1 Spot Size 33
3.4.18.1.2 Effective Area 33
3.4.18.1.3 f/number 33
3.4.18.2 X-ray Rehearsal Optic Mount 33
3.4.18.2.1 Postitioning 33
3.4.18.2.2 Stability 33
4 ALIGNMENT/STABILITY REQUIREMENTS AND ALLOCATIONS 34
4.1 HRMA TO FACILITY OPTICAL AXIS 34
4.1.1 AXIAL LOCATION 34
4.1.2 LATERAL DECENTRATION OF HRMA NODAL
POINT: 34
4.1.3 TILT OF THE HRMA OPTICAL AXIS: 34
4.1.4 HRMA CLOCKING 34
4.2 HRMA TO OTG 35
4.2.1 Static Alignment Tolerances 35
4.2.1.1 Static Alignment in X 35
4.2.1.2 Static Decenter 35
4.2.1.3 Static Alignment in Rotation About
X 35
4.2.1.4 Static Alignment in Rotation About
Y 35
4.2.1.5 Static Alignment in Rotation About
Z 35
4.2.2 Stability Tolerances 35
4.2.2.1 Stability in X 35
4.2.2.2 Decenter Stability 35
4.2.2.3 Stability in Rotation About X 35
4.2.2.4 Stability in Rotation About Y 36
4.2.2.5 Stability in Rotation About Z 36
4.2.3 Repeatability Tolerances 36
4.2.3.1 Repeatability in Despace 36
4.2.3.2 Repeatability in Decenter 36
4.2.3.3 Repeatability in Rotation About X36
4.2.3.4 Repeatability in Rotation About Y36
4.2.3.5 Repeatability in Rotation About Z36
4.3 ENVIRONMENT 37
4.3.1 Stray Light 37
4.3.2 Microseismic Vibration 37
4.3.3 Vacuum 37
4.3.4 Thermal 37
5 WORKMANSHIP STANDARDS 38
5.1 BAKEOUT 38
5.1.1 Surface Cleanliness Levels 38
5.2 TRAPPED VOLUMES 39
6 GLOSSARY OF TERMS 40
7 ACRONYMS 41
1 1 SCOPE1 SCOPE
It is the scope of this document to state the requirements for
the ground support equipment (GSE) needed to calibrate the
Advanced X-ray Astrophysics Facility-Imaging (AXAF-I) high
resolution mirror (HRMA) and its science complement of science
instruments (SI). This calibration activity is to be carried out
at the George C. Marshall Space Flight Center (MSFC) in the x-ray
calibration facility (XRCF).
2 APPLICABLE DOCUMENTSPPLICABLE DOCUMENTS
2.1 REQUIRED DOCUMENTS REQUIRED DOCUMENTS
2.1.1 Team Member DocumentsTeam Member Documents
MSFC
MSFC-SPEC-1238 Thermal Vacuum Bakeout Specification for
Contamination Sensitive Hardware
MSFC-SPEC-1837 AXAF X-ray Test Calibration Facility
Requirements
MSFC-SPEC-1839 AXAF X-ray HRMA/SI Calibration
Requirements
MSFC-RQMT-2229 Scientific Requirements for AXAF-I
Calibration
FAC-EJ-4708 XRCF Specification and Drawing Package
MSFC-SPEC-2401 End Item Specification for the X-ray
Calibration Facility X-ray Source System
TRW Documents
DPD 692 XC05 XRCF GSE Interface Definition Document
DPD 692 SE28 AXAF Contamination and Control Plan
EQ16-0057 Equipment Specification for Command
Telemetry Unit Emulator
D17830 Motion Detection System Requirements
DR XC02 VETA-I Calibration Requirements.
TRW Drawings
E445905 XRCF Coordinate System
E445907 Architectural Coordinate System
E445908 MDS Coordinate System and Sign
Convention
E445909 HRMA Shutter Blade Designations
E445910 Alignment Telescope Assembly Coordinate
System
E445900 XRCF Data System
2.1.2 Government Specificationsovernment Specifications
Federal
FED-STD-209 Clean Room and Work Station
Requirements, Controlled Environment
Military
MIL-STD-1246 Product Cleanliness Levels and
Contamination Control Program
3
REQUIREMENTSEQUIREMENTS
3.1 COORDINATE SYSTEMOORDINATE SYSTEM
There are many coordinate systems used in the execution of x-ray
test activities. It is important that the relationships among
the various systems be well understood in order to facilitate
proper and accurate communication among team members.
3.1.1 XRCFRCF
The XRCF coordinate system is defined in TRW drawing (DWG)
E445905.
3.1.2 Architectural Coordinate Systemrchitectural Coordinate
System
The architectural coordinate system (ACS) is based upon surveying
datum used in the design of the XRCF. The ACS is based on
stations (STA) located 100 feet apart on the guide tube (GT)
centerline. The west end of the GT is denoted as STA 27+01.5 and
the station number decreases to the east. This coordinate system
is shown in DWG E445907 and is used primarily to assign positions
of GT features.
3.1.3 MDSDS
The MDS coordinate system is used to reckon the relative motion
data reported by the MDS. The axes of the MDS coordinate system
are parallel to but displaced from the XRCF coordinate system
defined above. The MDS X axis is parallel to the XRCF X axis and
is defined by the line in the XRCF coordinate system Y=-4.76
inches, Z=-2.75 inches. The MDS Y and Z axes are parallel to the
respective XRCF axis. The MDS origin is at the OPS, located
proximate to the focal plane of the HRMA. The axial displacement
of the origin is irrelevant since the MDS can only reckon
relative motion in the MDS or XRCF (Y, Z) plane.
The MDS coordinate system and sign convention are given in DWG
E445908.
3.1.4 ATATA
The ATA coordinate system is defined when the ATA is used as an
autocollimator to measure the HRMA line of sight (LOS) is shown
in E445910. The ATA measures the rotation angle of the normal to
the alignment reference mirror (ARM) about the XRCF Y axis, qY,
and the rotation about the XRCF Z axis, qZ. The correctly
reckoned signs for the rotations are shown in E445910,
corresponding to the two rotation angles when viewed through the
ATA eyepiece reticle.
3.1.5 SCIENCE INSTRUMENT MODULE FIVE AXIS MOUNTCIENCE
INSTRUMENT MODULE FIVE AXIS MOUNT
The coordinate system for the science instrument module (SIM)
five axis mount (FAM) is TBD.
3.1.6 HRMARMA
The coordinate system for the HRMA is defined in EK-5003-100,
section 3.3.11 and Figure 3.3.11-1.
3.1.7 HRMA X-ray Detection SystemRMA X-ray Detection System
The HXDS coordinate system has its axes parallel (to within its
alignment tolerances) to the corresponding axes of the XRCF
coordinate system. The origin of the HXDA coordinate system is
located at TBD.
3.2 UNITSNITS
3.2.1 Lengthength
Unless otherwise indicated, all dimensions in this document are
in feet and inches.
3.3 TIME DESIGNATIONIME DESIGNATION
If a time tag is not computer or IRIG generated, it shall be
noted with a suffix of "Z" at the end. For example, 1PM
Universal Time (UT) would be written, "1300Z".
3.4
SUBSYSTEM REQUIREMENTSUBSYSTEM REQUIREMENTS
3.4.1 MSFC SubsystemsSFC Subsystems
3.4.1.1 X-ray Calibration Facility-ray Calibration Facility
The MSFC XRCF is defined in MSFC-SPEC-1837.
3.4.1.2 X-ray Source System-ray Source System
The requirements for the x-ray source system (XSS) are given in
MSFC-SPEC-2229 and the "Draft Specification for the X-ray
Calibration Facility X-ray Source System."
3.4.1.2.1 Source Locationource Location
The source shall be located between STA 27+05+5.
3.4.1.2.2 Knowledge of Source Locationnowledge of Source Location
Knowledge of the source location shall be better than three
inches (TBR).
3.4.1.3 X-ray Monochrometer-ray Monochrometer
The requirements for the x-ray monochrometer (XM) are given in
MSFC-SPEC-2229.
3.4.1.4 Motion Detection Systemotion Detection System
The motion detection system (MDS) requirements are found in
D17830.
3.4.1.5 Autocollimating Telescope Assemblyutocollimating
Telescope Assembly
The ATA requirements can be found in DR XC02, VETA-I Calibration
Requirements.
3.4.1.6 Master Control Computeraster Control Computer
The Master Control Computer requirements are defined in AXAF
Master Control Computer System Requirements Specification, Final
Draft, December 2, 1993, and documents called out therein.
3.4.2 TRW SubsystemsRW Subsystems
3.4.2.1 Command Telemetry Unit Emulatorommand Telemetry Unit
Emulator
Detailed equipment specifications are found in EQ16-0057.
3.4.2.1.1 Functional Purposeunctional Purpose
The CTUE shall provide a common interface between the MCC, SI and
SIM EGSE and the SIs and ISIM RCTUs, as illustrated in TRW DWG
E445900.
3.4.2.1.2 Timing Signalsiming Signals
3.4.2.1.2.1 Frame Synchronizationrame Synchronization
The CTUE shall provide a science header synchronization pulse.
3.4.2.1.2.2 FPSI ClockPSI Clock
The CTUE shall provide a 1.024 MHz clock signal for FPSI use.
3.4.2.1.2.3 CTUE Clock StabilityTUE Clock Stability
The stability of the CTUE clock shall be better than 1 part in
108.
3.4.2.1.2.4 Facility Time StampFacility Time Stamp
The CTUE shall provide an IRIG B time stamp on each major frame.
3.4.2.1.3 Data Formatsata Formats
3.4.2.1.3.1 Number of Formatsumber of Formats
The CTUE shall provide data in flight telemetry formats per EQ16-
0057.
3.4.2.1.3.2 Display of Format in Useisplay of Format in Use
The CTUE shall display what format is in use.
3.4.2.1.3.3 Dissemination of Dataissemination of Data
The CTUE shall utilize point to point socket connection to
transmit commutated data to the SI and SIM EGSE and the MCC.
3.4.2.1.3.4 Data to the Master Control Computerata to the
Master Control Computer
The data delivered to the MCC shall contain the MCC header.
3.4.2.1.3.5 Data to the SI/SIM EGSEata to the SI/SIM EGSE
The data delivered to the SI/SIM EGSE shall not contain the MCC
header.
3.4.2.1.4 Network Interfaceetwork Interface
The CTUE shall have an ethernet interface to the SI and SIM EGSE
and the MCC
3.4.2.1.5 Interface Protocolnterface Protocol
The interface shall utilize TCP/IP socket protocol.
3.4.2.1.6 Cross Commandsross Commands
A cross command is defined as a syntactically correct command
that is issued fromEGSE console for instrument I to instrument J
(I¹J).
3.4.2.1.6.1 Veto of Cross Commandseto of Cross Commands
The CTUE shall prevent the issuance of cross-commands.
3.4.2.1.6.2 Cross Command Alarmross Command Alarm
The CTUE shall have a visible and audible display in case a cross
command is detected.
3.4.2.1.6.3 Command Inhibit on Detection of Cross
Commandommand Inhibit on Detection of Cross Command
The CTUE shall not issue any further commands in the block when a
cross command is detected.
3.4.2.1.6.4 Manual Restart on Cross Commandanual Restart on
Cross Command
The CTUE shall require a manual restart in the case of detected
cross command.
3.4.2.1.7 CTUE Security TUE Security
3.4.2.1.7.1 Password Accessassword Access
The CTUE shall have password access.
3.4.2.1.7.2 Command Acceptanceommand Acceptance
The CTUE will accept internal CTUE commands only from its
keyboard.
3.4.2.1.8 Proximity to RCTUsroximity to RCTUs
The CTUE shall be capable of being located at least 300 feet from
the target RCTUs.
3.4.3
EKC SubsystemsKC Subsystems
3.4.3.1 HRMA Support StructureRMA Support Structure
3.4.3.1.1 Weighteight
The weight of the HRMA and its Support structure shall be less
than 15,000 pounds.
3.4.3.1.2 Decentration and Initial Alignment Tilt
Toleranceecentration and Initial Alignment Tilt Tolerance
These tolerances are in section 0.
3.4.3.1.3 Remote Tilt Capability emote Tilt Capability
The HRMA support structure shall provide the capability to
remotely tilt the HRMA independently about either the Y or Z axis
through the nominal HRMA nodal point(pitch or yaw).
3.4.3.1.3.1 Remote Tilt Range-Pitchemote Tilt Range-Pitch
The HRMA Support structure shall be able to pitch the HRMA at
least +0.5° about the XRCF Y axis.
3.4.3.1.3.2 Remote Tilt Range-Yawemote Tilt Range-Yaw
The HRMA Support structure shall be able to yaw the HRMA at least
+1.5° about the XRCF Z axis.
3.4.3.1.3.3 Remote Tilt Accuracyemote Tilt Accuracy
The required knowledge of the angular position (radial) of the
HRMA optical axis relative to the facility optical axis (FOA)
shall be ± 10 (TBR) arcsecs up to 25 arcminute and can thereafter
degrade linearly up to 1 arcminute at 1.5°.
3.4.3.1.3.4 Remote Tilt Step Sizeemote Tilt Step Size
The required angular step size of the HRMA optical axis relative
to the centerline of the x-ray beam FOA 1shall be less than 10
arcsecs for both pitch and yaw.
3.4.3.1.3.5 Repeatability of Motionepeatability of Motion
Per 6/8/94 telecon I have told EKC to come back within 0.001 inch
in despace and 0.010 decenter. 5 arcmin in clocking.
3.4.3.1.3.5.1 Tip/Tiltip/Tilt
Per 6/8/94 telecon I have told EKC to come back within 0.001 inch
in despace and 0.010 decenter. 5 arcmin in clocking.
The required accuracy of the repeatability of motion of the HRMA
optical axis relative to the FOA shall be + 20 arcsec for both
pitch and yaw.
3.4.3.1.3.5.2 Despaceespace
Per 6/8/94 telecon I have told EKC to come back within 0.001 inch
in despace and 0.010 decenter. 5 arcmin in clocking.
The required accuracy of the repeatability of motion of the HRMA
optical axis relative to the FOA shall be less than 0.001 inch in
depsace.
3.4.3.1.3.5.3 Decenterecenter
Per 6/8/94 telecon I have told EKC to come back within 0.001 inch
in despace and 0.010 decenter. 5 arcmin in clocking.
The required accuracy of the repeatability of motion of the HRMA
optical axis relative to the FOA shall be less than 0.010 inch in
decenter.
3.4.3.1.3.5.4 Clockinglocking
Per 6/8/94 telecon I have told EKC to come back within 0.001 inch
in despace and 0.010 decenter. 5 arcmin in clocking.
The required accuracy of the repeatability of motion of the HRMA
optical axis relative to the FOA shall be less than 5 arcminutes
in clocking.
3.4.3.1.4 Rotation Angle Axis Locationotation Angle Axis Location
Both the horizontal and vertical HRMA support structure rotation
axes shall be within +/- 1.0 (TBR) inches of the HRMA nodal
point.
3.4.3.1.5 Orientation Reportingrientation Reporting
The position of the HRMA shall be reported to the MCC in a timely
and accurate manner after each change of orientation. (TBR).2
3.4.3.1.6 Repositioning Rateepositioning Rate
The time for the HRMA Support structure to orient the HRMA to any
new position within 30 arcminutes (radial)shall not exceed 3
(three) minutes.
3.4.3.1.7 Stability tability
The following paragraphs give the requirements for the mechanical
stability of the nominal HRMA node point due to mechanical
vibration and thermal causes in the HSS3. The ambient
environment inside the instrument chamber is defined as 50±1°F
and a pressure range of 760 to 10-6 torr.
3.4.3.1.7.1 Thermal Stabilityhermal Stability
Thermal induced changes are assumed to have a frequency of less
than 0.1 Hz. It is assumed that the XRCF is performing per MSFC-
SPEC-1837.4
3.4.3.1.7.1.1 Transverse Stabilityransverse Stability
The HRMA support structure contribution to the Y-Z plane motion
of the HRMA node due to thermal causes shall not exceed 0.000481
inches/axis during any 24 hour time interval.
3.4.3.1.7.1.2 Axial Stabilityxial Stability
The HRMA support structure contribution to motion along the
X-axis of the x-ray detector due to thermal effects shall not
exceed 0.00095 inches during any 24 hour time period.
3.4.3.1.7.2 Vibration Induced Motionibration Induced Motion
Vibration induced motions are assumed to have a frequency of 0.1
Hz or greater.
3.4.3.1.7.2.1 Transverse Stabilityransverse Stability
The HRMA support structure contribution to the Y-Z plane motion
of the HRMA node due to vibration shall not exceed 0.000095
inches/axis.
3.4.3.1.7.2.2 Axial Stabilityxial Stability
The HRMA support structure contribution to motion along the
X-axis of the x-ray detector due to thermal effects shall not
exceed 0.00075 inches during any 24 hour time period.
3.4.3.2 HRMA Forward Contamination CoverRMA Forward
Contamination Cover
The HRMA shall have a forward contamination cover which has the
capability of being remotely and independently opened or closed
over the forward (toward x-ray source) end of the HRMA.
3.4.3.2.1 Obscuration of X-ray Beambscuration of X-ray Beam
When opened, the forward contamination cover shall not obscure or
scatter any of the x-ray radiation being transmitted to the focal
plane for the total HRMA clear aperture.
3.4.3.2.2 Time to Openime to Open
The time required to open the forward contamination cover shall
be no greater than 10 (ten) minutes.
3.4.3.3 HRMA Aft Contamination CoverRMA Aft Contamination Cover
The HRMA shall have an aft contamination cover which has the
capability of being remotely and independently opened or closed
over the aft (away from the x-ray source) end of the HRMA.
3.4.3.3.1 Obscuration of X-ray Beambscuration of X-ray Beam
When opened, the aft contamination cover shall not obscure or
scatter any of the x-ray radiation being transmitted to the focal
plane from the total HRMA clear aperture.
3.4.3.3.2 Time to Openime to Open
The time required to open the aft contamination cover shall be no
greater than 10 (ten) minutes.
3.4.3.4 Purge Capabilityurge Capability
The HRMA internal pressure shall be equal to or greater than the
ambient pressure of the IC during pressurization,
depressurization and ambient pressure phases.
3.4.3.5 OTG MountTG Mount
The OTG mount and insertion/retraction mechanism shall mount to
the HRMA support structure just to the rear of the HRMA
postcollimator. This structure shall provide the following
functions:
1. Support the 2 OTGs during x-ray calibration of the
FPSIs.
2. Provide for the remote insertion and retraction of
the OTGs during x-ray test.
3.4.3.5.1 OTG Position Requirements TG Position Requirements
The OTG mount & insertion/retraction mechanism shall be capable
of positioning either of the OTGs into the x-ray beam behind the
HRMA, perpendicular to the HRMA axis, centered on the HRMA axis
with the roll angle of the grating surface about the HRMA optical
axis set to a predetermined value.
3.4.3.5.2 OTGs in UseOTGs in Use
Only one OTG shall be in the x-ray beam at a time.
3.4.3.5.3 Obscuration of X-ray Beam by Retracted OTGbscuration of
X-ray Beam by Retracted OTG
When retracted they shall not obscure the x-ray line of sight
from the HRMA to the FPSIs over the entire HRMA clear aperture.
3.4.3.5.4 OTG Alignment Tolerances TG Alignment Tolerances
OTG static alignment tolerances are given in section 0.
3.4.3.5.4.1 OTG Stability TolerancesTG Stability Tolerances
OTG stability tolerances are given in section 0.
3.4.3.5.4.2 OTG Repeatability TolerancesTG Repeatability
Tolerances
OTG stability tolerances are given in section 0.
3.4.3.5.5 Insertion/Retraction Timensertion/Retraction Time
The OTG mount shall be able to insert or retract either OTG in 3
(three) minutes.
3.4.3.5.6 Position Feedbackosition Feedback
The OTG mount shall provide a means of determining the status
(inserted or retracted) for each OTG.
3.4.3.5.7 OTG Insertion/Retraction Speed and AccelerationTG
Insertion/Retraction Speed and Acceleration
The rate at which the OTGs are inserted and retracted shall not
impart loads to the OTGs that exceed 80% of maximum flight loads.
3.4.3.6 Movement of the Aft Contamination Cover and OTGsovement
of the Aft Contamination Cover and OTGs
The remotely operated control system governing the movement of
the ACC and the OTGs shall permit travel of only one unit at a
time.
3.4.3.7
HRMA Shutter AssemblyRMA Shutter Assembly
The HRMA shutter assembly shall mount to the HRMA support
structure and shall be located between the HRMA and the focal
plane. This assembly shall provide the following functions:
1. Shutter the clear x-ray aperture of all but a
given P/H mirror pair, for each mirror pair.
2. Shutter the clear x-ray aperture of that mirror
pair so that only one of four 90° 8815annular
quadrant sectors centered on the HRMA is clear and
transmitting x-ray energy.
3. The shutter quadrants shall be oriented such that
they are symmetric with respect to the Y and Z axes.
4. Each individual shutter blade shall operate
independently of the open/closed status of any and all
of the other shutters.
3.4.3.7.1 Shutter Blade ClockingShutter Blade Clocking
The HSA shall be aligned to the facility coordinate system such
that the compound angle between the HSA X axis and the FOA is
less than 1°. Knowledge of this clocking shall be 5 arcminutes
or less.
3.4.3.7.2 Shutter Blade DesignationShutter Blade Designation
The designations for the shutter blades is defined in DWG
E445909.
3.4.3.7.3 Simultaneity of Shutter Operationimultaneity of Shutter
Operation
Any combination of individual shutter blades shall be capable of
being simultaneously operated.
3.4.3.7.4 Remote Operationemote Operation
The HRMA shutter assembly shall provide the capability to be
remotely operated.
3.4.3.7.5 Time to Reconfigureime to Reconfigure
The time required to reconfigure the HSA shall be no greater than
10 seconds.
3.4.3.7.6 Obscuration of x-ray beambscuration of x-ray beam
When any x-ray shutter is open, it shall not obscure or scatter
any of the x-ray radiation being transmitted to the focal plane
for the desired clear aperture.
3.4.3.7.7 Shutter Opacityhutter Opacity
The HSA blades shall have an opacity to x-rays between 80 eV and
10 keV equal to 0.115 inches of aluminum.
3.4.3.7.8 Position Feedbackosition Feedback
The HSA shall provide a means of determining the status (open or
closed) of the shutter assembly.
3.4.3.7.9 HSA Control InterfaceHSA Control Interface
The HSA shall be controlled from SAO supplied equipment. The
interface is documented in XC05.6
3.4.3.8 1-g Offloader-g Offloader
The 1-g off-loader will shall as a goal7 limit the difference due
to 1g effects between on-orbit and ground encircled energy at any
diameter greater than or equal to 0.010 mm and centered on the
on-axis focal point to 15% (TBR) of the on-orbit value with
uncertainty less than 5% (TBR) of the on-orbit value.
3.4.4 SAO Subsystems SAO Subsystems
3.4.4.1 HRMA X-ray Detector SystemRMA X-ray Detector System
A collection of specialized detectors, the HXDS, shall be
developed and operated for x-ray calibration rehearsal, HRMA and
HRMA/SI calibration.
3.4.4.1.1 Image Plane Detectorsmage Plane Detectors
Detectors at the HRMA entrance aperture in the instrument chamber
shall include the image plane proportional counters with variable
apertures image plane solid-state detectors with apertures and,
an image plane high speed imager. Detailed requirements can be
found in MSFC-SPEC-2229.
3.4.4.1.2 Beam Normalization Detectorseam Normalization Detectors
BNDs shall include the following.
3.4.4.1.2.1 BND-500ND-500
Beam normalization detectors shall be required at building 500.
Detailed requirements can be found in MSFC-SPEC-2229.
3.4.4.1.2.2 BND-HND-H
Beam normalization detectors shall be required in the Instrument
Chamber at the HRMA entrance aperture. Detailed requirements can
be found in MSFC-SPEC-2229.
3.4.5
BECD Subsystems
3.4.5.1 Five Axis Mountive Axis Mount
a. provide mechanical interfaces between the ISIM and XRCF
provided detector end test bench
b. provide a proper thermal interface between the ISIM and XRCF
c. provide remotely operated and controlled 5 degree of freedom
(DOF) motion control of the ISIM, specifically translation in the
±X, ±Y and ±Z directions and rotation about the Y and Z axes.
d. provide initial alignment capability in all 6 DOF
e. provide a mechanical interface for the GFE motion detection
system optical point source
f. records history of ISIM positioning in the x-ray focal plane
g. records and controls ISIM temperatures.
h. provide an MDS interface.
3.4.5.2 Physical Requirementshysical Requirements
3.4.5.3 Envelopenvelope
The FAM will be installed in the instrument chamber and must
remain within the space and volume envelope as defined in DWG
E445700 sheet 2 and sheet 3, view JJ and KK. DWG E445700 can be
found in DR XC05, Book 2.
3.4.5.4 Weighteight
The weight of the FAM shall be less than 12,000 pounds.
3.4.5.5 Load Test Load Test
The FAM shall be proof tested per MSFC-STD-126E.
3.4.5.6 Failures Failures
There shall be no credible failure modes which could propagate
across the interface to the ISIM and cause the failure or loss of
the ISIM.
3.4.5.7 MDS Source AccommodationDS Source Accommodation
3.4.5.7.1 Location of Source Location of Source
The MDS source shall be located at the following location as
expressed in the XRCF coordinate system:
X= -373 ± 10 inches
Y= -4.76 ± 0.050 inches
Z= -2.75 ± 0.050 inches.
3.4.5.7.2 Source Interface Location Stability Relative to SI Aim
Pointource Interface Location Stability Relative to SI Aim Point
The interface for the MDS source shall maintain the source
relative position with respect to a given SI aim point to within
±50 µm in the X direction and 1.50 µm radial in the transverse
(Y-Z) plane, as a goal, for periods of up to 2 hours.
3.4.5.8 External Thermal Interfacexternal Thermal Interface
The Cryoshround Assembly (CSA) shall be designed so as to not
prevent the establishment of the a thermal condition of 50° ± 2°F
within the instrument chamber.
3.4.5.9 Internal Thermal Interfacenternal Thermal Interface
The CSA shall simulate the space thermal environment such that
the heat generated in the SIM is adequately removed.
3.4.5.10 Operating Modesperating Modes
The operating mode shall be selectable from the FAM control
console.
3.4.5.11 Static Modetatic Mode
In the static mode, the FAM is commanded to a fixed position.
The FAM remains stationary subject to the relevant specifications
contained herein.
3.4.5.12 Motionotion
The FAM must be able to translate the SIM with the following
characteristics:
3.4.5.12.1 X-axis: Range-axis: Range
The X- axis range shall be at least ±1.0 inches. The range of
motion is to be centered about the HRMA finite conjugate focal
point.
3.4.6 Initial Alignment to Facility Optical Axisnitial
Alignment to Facility Optical Axis
The ISIM shall be aligned to the facility optical axis (FOA) to
the tolerances given in the following paragraphs.
3.4.6.1 Initial Alignment in Xnitial Alignment in X
The FAM shall place the ISIM within 0.100 inches of the nominal
focal point.
3.4.6.2 Initial Lateral Alignmentnitial Lateral Alignment
The FAM shall place the ISIM such that the initial focal plane
aim point lateral offset (Y-Z plane) is within 0.100 inches
(radial) of the nominal focal point of the HRMA.
3.4.6.3 Initial Alignment of Normal to SIM Focal Planenitial
Alignment of Normal to SIM Focal Plane
The FAM shall align the normal of the SIM focal plane to within
120 arcseconds (radial) of the FOA.
3.4.6.4 Initial Rotation about FOAnitial Rotation about FOA
The FAM shall align the ISIM such that the line containing the
nominal SI aim points forms an angle of 90°±0.25° with respect
to the XRCF Y axis.
3.4.6.5 X-axis: Mechanism Resolution-axis: Mechanism Resolution
The X-axis step size shall be no larger than 0.0005 inches.
3.4.6.6 X-axis: Position Sensor Resolution-axis: Position
Sensor Resolution
The X-axis step resolution shall be no larger than 0.0005 inches.
3.4.6.7 X-axis: Rate-axis: Rate
The rate of translation in the X-axis shall be at least 0.1
inch/minute.
3.4.6.8 Y-axis: Range -axis: Range
The Y-axis range shall be at least ±7 inches. The range of motion
is to be centered about the HRMA finite conjugate focal point.
3.4.6.9 Y-axis: Step Size-axis: Step Size
The Y-axis step size shall be no larger than 0.005 inches.
3.4.6.10 Y-axis: Resolution-axis: Resolution
The Y-axis step size resolution shall be no larger than 0.005
inches.
3.4.6.11 Y-axis: Rate-axis: Rate
The rate of translation in the Y-axis shall be at least 1
inch/minute.
3.4.6.12 Z-axis: Range-axis: Range
The range of motion shall be arranged such that each SI can be
located ±7 inches (±1°) from the nominal HRMA finite conjugate
focal point in the Z direction.
3.4.6.13 Z-axis: Step Size-axis: Step Size
The Z-axis step size shall be no larger than 0.005 inches.
3.4.6.14 Z-axis: Resolution-axis: Resolution
The Z-axis step size resolution shall be no larger than 0.005
inches.
3.4.6.15 Z-axis: Rate-axis: Rate
The rate of translation in the Z-axis shall be at least 1
inch/minute.
3.4.6.16 Dither Modeither Mode
The ISIM FAM dither mode is intended to be a simulation of the
spacecraft dither mode. In this operating mode the image is
spread accross the focal place by a series of small movements.
In the XRCF this will be accomplished by driving the ISIM to the
desired location and invoking a dither program. This will move
the ISIM in small steps dwelling at each location for a
commandable periods of time, before slewing to the next position.
3.4.6.16.1 Step Sizetep Size
The step size, d, for the dither mode shall be 11±1 mm
(0.433±0.040 mil)
3.4.6.16.2 Range of Capabilityange of Capability
The dither mode shall be capable of operation at any location
over the full FAM range.
3.4.6.16.3 Positonal Accuracy-Absoluteositonal Accuracy-
Absolute
When commanded, the SIM shall go to the commanded position ±1
step.
3.4.6.16.4 Postional Accuracy-Relative to Starting
Positionostional Accuracy-Relative to Starting Position
The relative accuracy (per axis) in the knowlegde of the
posistion of the SIM shall be ±2mm for any 2 mm sub-range.
3.4.6.16.5 Dwell Time
The dwell time at each location shall be specified in a data file
in seconds supplied by the FPSI teams prior to x-ray calibration.
3.4.6.16.6 Motion Controlotion Control
The FAM dither mode shall be capable of commanding the FAM to
begin from a location, move to another and dwell for a specified
period of time. The FAM control software shall receive data from
an FPSI supplied data file. The data file shall contain a list
of ASCII values giving the Y and Z coordinates relative to the
current location, and the dwell time in seconds at each location.
3.4.6.16.7 Data ata
3.4.6.16.7.1 Data Displayata Display
The SIM control console shall display the position of the SIM in
near real time.
3.4.6.16.7.2 Data Transmissionata Transmission
At the conclusion of a dither measurement sequence, the data
history of postions, dwell and slew times and all other relevant
data shall be IRIG time stamped and archived to the MCC.
3.4.7
Stability tability
The following paragraphs give the requirements for the mechanical
stability of the nominal SIM aim point due to mechanical
vibration and thermal causes. The ambient environment inside the
instrument chamber is defined as 50±1°F and a pressure range of
760 to 10-6 torr.
3.4.7.1 Thermal Stabilityhermal Stability
Thermal induced changes are assumed to have a frequency of less
than 0.1 Hz.
3.4.7.1.1 Transverse Stabilityransverse Stability
The FAM contribution to the Y-Z plane motion of the x-ray
detector due to thermal causes shall not exceed 0.000481
inches/axis during any 24 hour time interval.
3.4.7.1.2 Axial Stabilityxial Stability
The FAM contribution to motion along the X-axis of the x-ray
detector due to thermal effects shall not exceed 0.00095 inches
during any 24 hour time period.
3.4.7.2 Vibration Induced Motionibration Induced Motion
Vibration induced motions are assumed to have a frequency of 0.1
Hz or greater.
3.4.7.2.1 Transverse Stabilityransverse Stability
The FAM contribution to the Y-Z plane motion of the x-ray
detector due to vibration shall not exceed 0.000095 inches/axis.
3.4.7.2.2 Axial Stabilityxial Stability
The FAM contribution to motion along the X-axis of the x-ray
detector due to vibration induced motions shall not exceed
0.00075 inches during any 24 hour time period.
3.4.8 Rotation
The FAM must be able to rotate the SIM with the following
characteristics:
3.4.8.1 X-axis: Rotation-axis: Rotation
Rotation of about the X-axis is not required.
3.4.8.2 Y-axis: Range-axis: Range
The range of rotation about the Y- axis shall be at least ±1°.
3.4.8.3 Y-axis: Step Size-axis: Step Size
The step size in rotation about the Y-axis shall be no greater
than 10 arcsecs.
3.4.8.4 Y-axis: Resolution-axis: Resolution
The resolution of angular orientation in rotation about the Y
axis shall be no larger than 10 arcsecs.
3.4.8.5 Y-axis: Rate-axis: Rate
At least 0.1 degree/minute.
3.4.8.6 Z-axis: Range-axis: Range
The range of rotation about the Z- axis shall be at least ±1°.
3.4.8.7 Z-axis: Step Size-axis: Step Size
The step size in rotation about the Y-axis shall be no greater
than 10 arcsecs.
3.4.8.8 Z-axis: Resolution-axis: Resolution
The resolution of angular orientation in rotation about the Y
axis shall be no larger than 10 arcsecs.
3.4.9 FAM Controller SoftwareAM Controller Software
3.4.9.1 Communicationommunication
The FAM controller must be able to communicate with the MSFC
supplied Master Control Computer. (MCC) The MCC issues messages
to the target system via ethernet to queue test activity. Upon
receipt of the message, the operator of the FAM will respond
appropriately. The FAM controller should also reply to the
messages as tasks are completed. Thus, it is recommended that
the operating system for the FAM controller be a multitasking
windows capable system.
3.4.9.2 Data Recordingata Recording
A full history of positional sensor and thermal data shall be
maintained. These records will be transferred to the MCC, which
is also on the LAN.
3.4.10 ACIS Cryogenic InterfaceCIS Cryogenic Interface
The SIM shall accommodate the ACIS cryogenic interface.
3.4.11 Accessccess
The SIM shall accomodate access to the ACIS high speed data
connector.
3.4.12 Vacuum Interfaceacuum Interface
The SIM shall provide an interface for vacuum capability.
3.4.13
HRC SubsystemsRC Subsystems
3.4.13.1 Electrical Ground Support Equipment-HRClectrical Ground
Support Equipment-HRC
3.4.13.1.1 Command Validationommand Validation
The HRC electrical GSE (EGSE) shall validate all commands sent to
the HRC.
3.4.13.1.2 Telemetry Decommutationelemetry Decommutation
The HRC EGSE shall be able to decommutate any and all data
necessary to operation of the HRC that is transmitted to it by
the CTUE.
3.4.13.2 Verificationerification
The HRC is responsible for critical command verification.
3.4.13.3 Command Formatommand Format
The HRC shall be compatible with the command format given in
paragraph 3.2.1.2.3 of EQ16-0057.
3.4.13.4 SI Command LogI Command Log
The HRC shall maintain a log of SI commands.
3.4.14 ACIS SubsystemsCIS Subsystems
3.4.14.1 Electrical Ground Support Equipment-ACISlectrical
Ground Support Equipment-ACIS
3.4.14.1.1 Command Validationommand Validation
The ACIS electrical GSE (EGSE) shall validate all commands sent
to the ACIS.
3.4.14.1.2 Telemetry Decommutationelemetry Decommutation
The ACIS EGSE shall be able to decommutate any and all data
necessary to operation of the HRC that is transmitted to it by
the CTUE.
3.4.14.2 Verificationerification
The ACIS is responsible for critical command verification.
3.4.14.3 Command Formatommand Format
The ACIS shall be compatible with the command format given in
paragraph 3.2.1.2.3 of EQ16-0057.
3.4.14.4 SI Command LogI Command Log
The ACIS shall maintain a log of SI commands.
3.4.15 LETG SubsystemsETG Subsystems
TBD.
3.4.16 HETG SubsystemsETG Subsystems
TBD.
3.4.17 ASC SubsystemsSC Subsystems
TBD.
3.4.18
Other Systemsther Systems
3.4.18.1 X-ray Rehearsal Optic-ray Rehearsal Optic
The x-ray rehearsal optic (XSO) is to be used during the
rehearsal period. It purposes are to simulate the HRMA in such a
way that the test equipment, procedures and personnel my be
properly wrung out to facilitate an efficient operation during
HRMA and HRMA/SI calibration.
3.4.18.1.1 Spot Sizepot Size
The spot size (FWHM) of the XSO shall be between 25-40 mm.
3.4.18.1.2 Effective Areaffective Area
The effective area of the XSO shall be 20 cm2 or greater.
3.4.18.1.3 f/number/number
The f/number of the XSO shall be bewteen 10 and 16.
3.4.18.2 X-ray Rehearsal Optic Mount-ray Rehearsal Optic Mount
3.4.18.2.1 Postitioningostitioning
The XSO mount shall be capable of locating the XSO as defined in
0.
3.4.18.2.2 Stabilitytability
The XSO mount shall meet the stability requirements as called out
in 0.
4 ALIGNMENT/STABILITY REQUIREMENTS AND
ALLOCATIONSLIGNMENT/STABILITY REQUIREMENTS AND ALLOCATIONS
4.1 HRMA TO FACILITY OPTICAL AXISRMA TO FACILITY OPTICAL AXIS
The HRMA support structure shall provide the capability to
initially align the HRMA optical axis coincidentally with the FOA
prior to x-ray testing. The allowable initial alignment error
tolerances relative to the centerline of the x-ray beam FOA are
given below.
8
4.1.1 AXIAL LOCATIONXIAL LOCATION
Per telecon on 6/8/94 with Vallimont and Johnston value changed
to +/- 0.5 inch.
The axial location of the HRMA CAP mid-plane is at XXRCF = 0 ±
0.5 inch.
4.1.2 LATERAL DECENTRATION OF HRMA NODAL POINT:ATERAL
DECENTRATION OF HRMA NODAL POINT:
The HRMA support structure shall be capable of locating the HRMA
nodal point to within 0.1 inch (radial) of the facility optical
axis.
4.1.3 TILT OF THE HRMA OPTICAL AXIS:ILT OF THE HRMA OPTICAL
AXIS:
The HRMA shall be aligned such that the angle between the HRMA
optical axis and the facility optical axis is 15 arcsec (radial).
4.1.4 HRMA CLOCKINGRMA CLOCKING
Per telecon on 6/8/94 with Vallimont and Johnston value changed
to +/- 0.5 inch.
The HRMA shall be aligned such that the clocking angle about the
FOA is less than 32.5 arcminutes.
4.2 HRMA TO OTGRMA TO OTG
All alignment tolerances between the HRMA and OTGs are 3 sigma
tolerances.
4.2.1 Static Alignment Tolerancestatic Alignment Tolerances
The grating alignment references are a set of features located on
the OTGs. When the term GAR is used in the sections below it is
taken to mean the appropriate reference as called out on the OTG
interface control drawing, TRW DWG 301331. 9
4.2.1.1 Static Alignment in Xtatic Alignment in X
The GRIM shall locate the grating alignment reference (GAR) to ±
0.040 inch of its desired location in X.
4.2.1.2 Static Decentertatic Decenter
The GRIM shall locate the grating to within ±0.0174 inch of its
desired location in Y,Z plane.
4.2.1.3 Static Alignment in Rotation About Xtatic Alignment in
Rotation About X
The GRIM shall locate the GAR to within ±3.75 arcmin of its
desired location in rotation about X.
4.2.1.4 Static Alignment in Rotation About Y Tip/Tilttatic
Alignment in Rotation About Y
The GRIM shall locate the GAR to within ±2 arcmin of its desired
location in rotation about Y. The GRIM shall orient the GAR such
that the angle between the GAR-X axis and the FOA is less than
3.54 arcminutes.10
4.2.1.5 Static Alignment in Rotation About Ztatic Alignment in
Rotation About Z
The GRIM shall locate the GAR to within ±2 arcmin of its desired
location in rotation about Z./
4.2.2 Stability Tolerancestability Tolerances
4.2.2.1 Stability in Xtability in X
The GRIM shall maintain the GAR stable in the axial (X) direction
with respect to its intial axial location upon insertion to
within ± 0.0118 inch11.
4.2.2.2 Decenter Stabilityecenter Stability
The GRIM shall maintain the GAR stable in decenter (radial motion
in the Y,Z plane) with respect to its intial location upon
insertion to within ±0.0052 inch12.
4.2.2.3 Stability in Rotation About Xtability in Rotation About
X
The GRIM shall maintain the GAR stable in rotation about the X
direction with respect to its orientation upon insertion to
within ±1.125 arcminutes.
4.2.2.4 Stability in Rotation About YTip/Tilt13tability in
Rotation About Y
The GRIM shall maintain the GAR stable in rotation about the Y
direction with respect to its orientation upon insertion to
within ±0.5625 arcminutes.The GRIM shall maintain the orientation
to less than 1.06 arcminutes in tip/tilt.
4.2.2.4 Stability in Rotation About Ztability in Rotation About
Z
The GRIM shall maintain the GAR stable in rotation about the Z
direction with respect to its orientation upon insertion to
within ±0.5625 arcminutes.
4.2.3 Repeatability Tolerancesepeatability Tolerances
4.2.3.1 Repeatability in Despaceepeatability in Despace
The GRIM mechanism shall place the GAR in the axial (X) direction
with respect to its previous axial location upon insertion to
within ±0.0118 inch.
4.2.3.2 Repeatability in Decenterepeatability in Decenter
The GRIM mechanism shall place the GAR in the axial (X) direction
with respect to its previous axial location upon insertion to
within ±0.0052 inch14.
4.2.3.3 Repeatability in Rotation About Xepeatability in
Rotation About X
The GRIM mechanism shall place the GAR in rotation about the X
direction with respect to its orientation upon the previous
insertion to within ±1.125 arcminutes.
4.2.3.4 Repeatability in Rotation About Y Tip/Tilt15epeatability
in Rotation About Y
The GRIM mechanism shall place the GAR in rotation about the Y
direction with respect to its orientation upon the previous
insertion to within ±0.5625 arcminutes. The GRIM mechanism shall
have a repeatability of less than 1.06 arcminutes in tip/tilt.
4.2.3.5 Repeatability in Rotation About Zepeatability in
Rotation About Z
The GRIM mechanism shall place the GAR in rotation about the Z
direction with respect to its orientation upon the previous
insertion to within ±0.5625 arcminutes.
4.3 ENVIRONMENTNVIRONMENT
4.3.1 Stray Lighttray Light
The ambient stray light level within the IC at the x-ray detector
aperture shall be consistent with the stray light levels as given
in MSFC-SPEC-1836, paragraph 4.2.3.1.4. (NB: these levels apply
only when ACIS is in operation.)
4.3.2 Microseismic Vibration Fundamental
Frequencyicroseismic Vibration
The power spectral density of typical XRCF disturbances is given
in DR XCO5. All GSE shall have a fundamental frequency in excess
of 4 Hz.16
4.3.3 Vacuumacuum
The vacuum environment of the IC shall meet the requirements
given in MSFC-SPEC-1837.
4.3.4 Thermalhermal
The thermal environment of the IC shall meet the requirements
given in MSFC-SPEC-1837.
5
WORKMANSHIP STANDARDS WORKMANSHIP STANDARDS
The requirements contained in this section apply to all hardware
that will be resident in the instrument chamber.
5.1 BAKEOUTAKEOUT
All IC resident hardware shall be baked to remove volatiles.
This bakeout shall be in accordance with MSFC-SPEC-1238. This
"bake out" must occur prior to installation of the HRMA in the
XRCF vacuum chamber.
5.1.1 Surface Cleanliness Levelsurface Cleanliness Levels
All IC resident hardware shall be cleaned to a level of 350Å in
accordance with MIL-STD-1246.
5.2 TRAPPED VOLUMESRAPPED VOLUMES
All IC resident hardware shall have no trapped volumes that
preclude the achievement of an IC pressure level of 1x10-6 torr
in 24 hours.
6
GLOSSARY OF TERMS GLOSSARY OF TERMS
Aimpoint: Any point on either active focal
plane of either FPSI.
Resolution, Mechanism: The minimum controllable motion
interval that the system is capable of producing.
Resolution, Sensor: The minimum motion interval that
the sensor is capable of reporting.
Repeatability, Mechanisms, The extent to which successive
attempts to move to a specific
Uni-directional: location from a single direction
vary in position.
Repeatability, Mechanisms, The extent to which successive
attempts to move to a specific
Bi-directional: location from opposite directions
vary in position.
Repeatability, Sensor: The variation in reports by a
sensor system produced by successive movements to a specific
location.
Stability, Mechanical: The ability of a system to maintain
relative position of datums over a given range of environments
with the passage of time.
Stability, Sensors: The ability of a sensor system to
report the same measurement when measuring an unchanged quantity
over a given range of environments with the passage of time.
Accuracy, Mechanism: The degree to which displacements
executed by a positioning system match agreed upon standards.
Accuracy, Sensor: The degree to which displacements
measured by a system match agreed upon standards.
7
ACRONYMSCRONYMS
ACIS
AXAF CCD Imaging Spectrometer 26, 27, 29, 37
ACS
Architectural Coordinate System 4
ARM
Alignment Reference Mirror 4
ATA
Alignment Telescope Assembly 4, 8
BECD
Ball Electro-Optics and Cryogenics Division 20
BND
Beam Normalization Detector 19
CAP
Center Aperture Plate 34
CTUE
CTU Emulator 9-11, 28, 29
DWG
Drawing 4, 9, 17, 20
EGSE
Electrical Ground Support Equipment 9, 10, 28, 29
EKC
Eastman Kodak Company 12
FAM
Five Axis Mount 5, 20-26
FOA
Facility Optical Axis 12, 13, 17, 21, 22, 34
FPSI
Focal Plane Science Instrument 9, 24, 40
FWHM
Full Width Half Maximum 33
GFE
Government Furnished Equipment 20
GSE
Ground Support Equipment 1, 2, 28, 29
GT
Guide Tube 4
HETG
High Energy Transmission Grating 31
HRC
High Resolution Camera 28, 29
HRMA
High Resolution Mirror Assembly 1, 2, 4, 5, 12-15, 17, 19, 21-23, 33-35,
38
HXDA
HRMA X-ray Detector Assembly 5
HXDS
HRMA X-ray Detection System 5, 19
IC
Instrument Chamber 15, 37-39
ICVS
Instrument Chamber Vacuum System 10
IRIG
Intra Range Instrumentation Group 7, 9, 24
ISIM
Intergrated Science Instrument Module 9, 20-23
LETG
Low Energy Transmission Grating 30
LOS
Line of Sight 4
MCC
Master Control Computer 9, 10, 13, 24, 26
MDS
Motion Detection System 2, 4, 8, 20, 21
MSFC
Marshall Space Flight Center 1, 2, 8, 19, 20, 26, 37, 38
OPS
Optical Point Source 4
OTG
Optical Transmission Grating 15, 16, 35
P/H
Paraboloid/Hyperboloid 17
SAO
Smithsonian Astrophysical Observatory 19
SI
Science Instrument 1, 2, 9, 10, 19, 21-23, 28, 29, 33
SIM
Science Instrument Module 5, 9, 10, 21-25, 27
STA
Station 4, 8
TBD
To Be Determined 5, 30-32
TBR
To Be Resolved 8, 12, 13, 18
TRW
TRW Incorporated 1, 2, 4, 9
XRCF
X-ray Calibration Facility 1-5, 8, 12, 20-23, 37, 38
XSO
X-ray Surrogate Optic 33
_______________________________
1XRCCOM-14
2Remove TBR, this is afterall a CDR version of requirements of
hardware that has been through CDA.
3XRCCOM-11
4XRCCOM-12
5XRCCOM-13
6XRCCOM-26
7 XRCCOM-10
8XRCCOM-14
9XRCCOM-16, 49 and 50 Proper text and reference to OTG ICD.
10XRCCOM-17 combine rotations and equate with flight
requirements.
11Missing units.
12Missing units.
13XRCCOM-17
14Missing units.
15XRCCOM-17
16XRCCOM-15This replacement of fundamental frequency for GSE for
definition of vibration spectrum was agreed to by all parties
involved as the simplest surest way to insure vibrational
stability at XRCF.