SPICA
FOCAL PLANE INSTRUMENT (FPI)
INTERFRACE CONTROL SPECIFICATIONS (ICS)
JAXA-SPICA-SYS-ICS-0002
January 8th, 2010 (draft)
Japan Aerospace Exploration Agency
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :2
Document Change Record
February 18, 2009
June 16, 2009
September 4, 2009
November 4, 2009
November 6, 2009
November 16,2009
November 16,2009
December 4-7, 2009
December 21, 2009
December 29, 2009
January 8, 2010
JAXA-SPICA-FPI0002 draft, First Edition
ICS-FPI working draft
ToC revised incl. AOCS requirement
AOCS described by Mitani-san
FPI-E resources updated
MIR, SCI operation modes added
FPI-E & thermal , optical resources are updated
FPI-E resources are updated
Release to pre-project team. Preliminary draft of AIV/T and
model philosophy is added. FPI cold volume updated. Document
ref. no. corrected.
FPI-E tables (page 40-41) are corrected
FPIA (FPI assembly) is now defined
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :3
List of Acronyms:
AT
Acceptance Test
BLISS
Background-Limited Infrared-Submillimeter Spectrograph
CRYO
Cryogenic Subsystem
FPC
Focal-Plane Camera for guider(-S), for science (-G)
FPI
Focal Plane Instruments
IOB
Instrument Optical Bench
IOBA
IOB assembly ( IOB & IOB bipods, pick-off mirror module
& 6K shield )
FPIA
FPI Assembly (=IOBA+FPI)
MIRACLE
Mid-InfRAred Camera w/o Lens
MIRMES
Mid-Infrared Medium-resolution Echelle Spectrometer
MIRHES
Md-infrared High-resolution Echelle Spectrometer
QT
Qualification Test
SAFARI
SPICA Far-infrared Instrument
SCI
SPICA Coronagraph Instrument
SPICA
Space Infrared Telescope for Cosmology and Astrophysics
STA
SPICA Telescope Assembly
DOC. No. : JAXA-SPICA-SYS-ICS-0002
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Table of Contents
1. Scope ......................................................................................................................................................................................... 6
2．Applicable Documents & Reference Documents ......................................................................................... 6
3. System Requirements ................................................................................................................................................... 6
3.1 FPI Description .......................................................................................................................................................... 6
3.1.1 Intruduction ........................................................................................................................................................ 6
3.1.2 MIRACLE ............................................................................................................................................................. 7
3.1.3 MIRMES................................................................................................................................................................ 8
3.1.4 MIRHES ................................................................................................................................................................ 8
3.1.5 SCI............................................................................................................................................................................. 8
3.1.6 SAFARI .................................................................................................................................................................. 9
3.1.7 BLISS ...................................................................................................................................................................... 9
3.1.8 FPC ........................................................................................................................................................................... 9
3.2. Pointing Control .....................................................................................................................................................10
3.2.1 Definitions ..........................................................................................................................................................10
3.2.2 Aspect Angle Constraints ........................................................................................................................11
3.2.3 Pointing Control Modes .............................................................................................................................12
4．FPIA Mechanical Interface Requirements....................................................................................................20
4.1 Overview .....................................................................................................................................................................20
4.2 Coordinate system .................................................................................................................................................20
4.2.1 Spacecraft Coordinate System ..............................................................................................................20
4.2.2 Spacecraft Body Coordinate System .................................................................................................21
4.2.3 IOB Coordinate System.............................................................................................................................22
4.2.4 FPI Coordinate System .............................................................................................................................22
4.2.5 FPC-G Coordinate System ......................................................................................................................22
4.3 Cold Volume, Mass requirement from FPIs .........................................................................................22
4.3 Mass property ...........................................................................................................................................................23
4.4. FPIA configuration ...............................................................................................................................................24
4.5 Disturbance Management ................................................................................................................................25
4.6.1 Disturbance Source in FPIA ..................................................................................................................25
4.6.2 Disturbance Susceptibility ......................................................................................................................25
4.6 Mounting Conditions ..........................................................................................................................................25
4.7 Alignment ..................................................................................................................................................................25
4.8 Surface Treatment and Surface Roughness .........................................................................................25
4.9 FPI Handling, Installation .............................................................................................................................25
5．FPIA Thermal Interface ............................................................................................................................................26
5.1 Overview .....................................................................................................................................................................26
5.2 Heat generation and thermal lift requirements ..............................................................................27
5.3 Parasitic Heat from Harness ........................................................................................................................36
6. FPIA Optical Interface ............................................................................................................................................38
6.1 Definitions ...................................................................................................................................................................38
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6.2 Field-of-view(FOV) configuration ................................................................................................................38
6.3 Alignment Requirements ..................................................................................................................................38
6.4 Aspect angle Constraints ..................................................................................................................................38
7．Electrical Interface .......................................................................................................................................................39
7.1 Overview .....................................................................................................................................................................39
7.2 Interface Connectors, Wire Harness ........................................................................................................39
7.3 FPI control Electronics (Warm) ..................................................................................................................39
7.4. SCI-AOCS I/F ..........................................................................................................................................................43
8. Onboard Data Handling Interface ......................................................................................................................43
8.1 Definitions ...................................................................................................................................................................43
8.2 Command Interface...............................................................................................................................................43
8.3 Telemetry Interface...............................................................................................................................................43
9. Dynamical Interface .....................................................................................................................................................43
9.1 Definitions ...................................................................................................................................................................43
9.2 Flexibility Parameters ........................................................................................................................................43
10. FPIA Development and Verification ...............................................................................................................43
10.1 Overview ....................................................................................................................................................................43
10.2 Model philosophy .................................................................................................................................................44
10.3 Analyses .....................................................................................................................................................................44
10.4 Testing ........................................................................................................................................................................44
10.4.1 Overview ...........................................................................................................................................................44
10.4.2 Electrical Functional Test Requirements...................................................................................44
10.4.3 EMC Test Requirements .......................................................................................................................44
10.4.4 Structural Test Requirements for FPIA ......................................................................................44
11. Product Assurance ......................................................................................................................................................45
12. Programme Requirements.....................................................................................................................................46
Appendices................................................................................................................................................................................46
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1. Scope
This document describes the interface conditions as well as the resource allocation for SPICA Focal
Plane Instrument (FPI) assembly (hereafter FPIA), namely mechanical, optical and thermal I/Fs
with the Cryogenic Subsystem (CRYO) and SPICA Telescope Assembly (STA), and also electrical
I/F (including resources for FPI warm electronics, such as power consumption according to their
operational modes) with the spacecraft bus system.
2．Applicable Documents & Reference Documents
[AD-1] JAXA-SPICA-SYS-ICS-0003
SAFARI Interface Control Specification (ICS-SAFARI)
[AD-2] ICS-BLISS
[AD-3] ICS-FPC
[AD-4] RSE-SP08001A
SPICA Mission Requirement Document
[AD-5] JAXA-SPICA-SYS-ICS-0001
INTERFACE CONDITIONS FOR SPICA TELESCOPE ASSEMBLY (STA)
[RD-1] JAXA-SPICA-IF0002
SPICA ENVIRONMENTAL CONDITIONS FOR SPICA TELESCOPE
ASSEMBLY (STA)
[RD-2] SPICA-FPI-2008-001
Request for Input to SPICA Focal Plane Instruments Resource Allocation Study
“Cycle-1” 2008/09/29
3. System Requirements
3.1 FPI Description
3.1.1 Intruduction
The Focal Plane Instruments (FPI) onboard SPICA shall be attached to the STA via the
Instrument Optical Bench (IOB, see Figure 4-1) which is thermally lifted at ~4.5K by a
J-T cooler.
The FPIs are consisted by following
MIRACLE (Mid-InfRAred Camera w/o Lens)
MIRMES (Mid-IR medium-resolution echelle spectrometer)
MIRHES (Mid-IR high-resolution echelle spectrometer
SCI (SPICA Coronagraph Instrument)
SAFARI (SPICA Far-infrared Instrument)
BLISS (Background-Limited Infrared-Submillimeter Spectrograph)
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FPC (Focal-plane finding camera)
3.1.2 MIRACLE
3.1.2.1 Instrument Hardware Overview
3.1.2.2 Operating Modes
MIRACLE consists of two channels (MIR-S and MIR-L), which will be operated
simultaneously (tbd).CPUs controlling MIRACLE may also handle MIRMES and
MIRHES (tbd). Here we tentatively describe the operation modes commonly defined for
MIRCLE, MIRMES, and MIRHES.
MODE: POWER-OFF
Primary power is shut-down, nothing are working in this mode.
MODE: STANDBY-1
Primary power is ON, instruments are not powered (waiting for power-ON), thus CPUs
are in HALT state. Command handling and HK data generation is in MINIMUM level.
MODE: STANDBY-2
CPU is running, instruments except for detectors are powered. Heat dissipation from
detector arrays to cold stages is SMALL (less than 10% of the FULL (see below).
Command handling is possible, HK data are FULLy generated. Electronics power is
also FULLy required (4W per detector array)
MODE: ON-1
Detectors are also powered, and operated normally. High-speed science data are not
generated, and no command requests for AOCS are generated. Heat dissipation to cold
stage is FULL (1mW per detector array).
MODE: ON-2
Mode for science observations. High-speed data are generated, and command requests
for AOCS are generated. Heat dissipation to cold stage is FULL (1mW per detector
array)
MODE: ANNEAL
Detectors are heated to ~20K in very short time in order to recover the bad pixels due to
the cosmic ray hit. The ammont of heat generation(OVER-FULL), dissipation
time-constant for the cold-stages are tbd.
Table 3.1-1 describes the change of the status of the Warm Electronics Power, Heat
Dissipation at Cold Stage, Command & HK data generation, and Science Data Generation,
according to the operation modes.
Table. 3.1-1 The status changes according to the MIRACLE operation modes
Mode
Warm Electronics
Power
Heat Dissipation
at Cold Stage
Command & HK
data generation
Science Data
Generation
POWER-OFF
OFF
OFF
OFF
OFF
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STANDBY-1
small (tbd)
OFF
MINIMUM
OFF
STANDBY-2
FULL
SMALL
FULL
OFF
ON-1
FULL
FULL
FULL
OFF
ON-2
FULL
FULL
FULL
ON
ANNEAL
FULL
Over-FULL
FULL
OFF
In any MIRACLE observations, the operation mode is “ON-2”, while, other observation is
under-way, MIRACLE is in stand-by with “ON-1” operation mode.
3.1.2.3 Observing Modes
Imaging-Mode
Spectroscopic-Mode(MIR-S)
Spectroscopic-Mode(MIR-L)
3.1.3 MIRMES
3.1.3.1 Instrument Hardware Overview
3.1.3.2 Operating Modes
Same as 3.1.2.2
3.1.3.3 Observing Modes
Spectroscopic-Mode (MIRMES Arm-Short)
Spectroscopic-Mode (MIRMES Arm-Long)
3.1.4 MIRHES
3.1.4.1 Instrument Hardware Overview
3.1.4.2 Operating Modes
Same as 3.1.2.2
3.1.4.3 Observing Modes
Spectroscopic-Mode (MIRHES S-mode）
Spectroscopic-Mode (MIRHES L-mode）
3.1.5 SCI
3.1.5.1 Instrument Hardware Overview
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3.1.5.1.1 SCI
3.1.5.1.2 C-FPC
C-FPC (Coronagraph Focal Plane Camera) is a special guide sensor for coronagraph
observation. The C-FPC detects a target star through the C-TTM and output an error
angle for pointing correction including C-TTM control error. Prior to initiating C-TTM
control, C-FPC output is feed forward to AOCS in order for the C-TTM to acquire the
target star within the C-TTM actuation range. After activating the C-TTM control,
C-FPC needs to detect both alignment error (low freq.) and mechanical disturbance
(high freq.). It is expected that the C-FPC can detect the mechanical disturbance in
high frequency, because it detects relatively bright stars for coronagraph observation.
3.1.5.1.3 C-TTM
C-TTM (Coronagraph Tip-Tilt Mirror) is a pointing control device dedicated for
coronagraph observation. The C-TTM can realize high pointing accuracy and high
pointing stability that cannot be achieved solely by a conventional AOCS. The C-TTM
is controlled by the error angle (including mechanical disturbance) detected by the
C-FPC.
3.1.5.2 Operating Modes
Mostly the same as 3.1.2.2., specific operating mode for SCI is under consideration.
3.1.5.3 Observing Modes
imaging-Mode
Spectroscopic-Mode
3.1.6 SAFARI
SAFARI’s instrument overview, operation & observation modes are described in [AD-1].
3.1.7 BLISS
BLISS’s instrument overview, operation & observation modes are described in [AD-2].
3.1.8 FPC
FPC’s instrument overview, operation & observation modes are described in [AD-3].
FPC-G (Focal Plane Camera for Guidance) is a guide sensor on board to the IOB
(Instrument Optical Bench), and it is commonly applied to all observations for improving
pointing accuracy and pointing stability. The FPC-G detects guide stars whose relative
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position to an target star is already known, and output the error angle by which target
star should be located in the center of a FPI sensor. The FPC-G is not capable of high
frequency output because it must detect faint stars, and hard to detect internal
mechanical disturbance due to such as cryogenic and starling coolers. More detail
information are described in [AD-3].
3.2. Pointing Control
3.2.1 Definitions
3.2.1.1 Definition of pointing performance
The required pointing performance are defined as follows. The coordinate system used
as reference is defined in section 4.2. Figure 3.2-1 illustrates relationship among the
pointing control accuracy, the pointing stability, and the pointing determination
accuracy in time domain.
•
•
•
The Pointing Control Accuracy is the angular separation between the true pointing
angle and the desired direction of the reference coordinate frame.
The Pointing Stability is the change of the angular separation between the true
pointing angle and the desired direction of the reference coordinate frame over a
given period of time.
The Pointing Determination Accuracy is the angular separation between the a true
pointing angle and the reconstructed direction (posteriori) of the reference
coordinate frame.
Fig.3.2-1 Time Domain Definitions
3.2.1.1 Definition of pointing settling time in step mode
DOC. No. : JAXA-SPICA-SYS-ICS-0002
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Pointing Settling Time in step mode is defined as the durarion time from the beginning
of step mode until the time when the condition to start the next pointing mode is
satisfied. poinitin settling time depends on step angle magnitude. The condition to
start the next pointing mode follows;
•
The condition in which pointing control error/pointing stability is within the
specified value continues more than thespecified time duration.
- In the case of sending attitude stability notification based on on-board
judgment, the condition is judged by on-board attitude determination values.
- The angle tolerance could be specified regardless of the pointing accuracy
and pointing stability requirement.
Pointing settling time
Angle
Time for settling judgment
Angle Tolerance
Time
Fig.3.2-1 Definition of pointing settling time in step mode
3.2.2 Aspect Angle Constraints
3.2.2.1 Sun angle constraints
During the nominal mission, one constraint is the roll angle defined as the rotation
around the Xs-axis being zero when the sun is in the Ys-Zs plane. This roll angle shall
be limited to +5 deg (no margin) (+Zs direction, towards the sun) and –30 deg (-Zs
direction, away from the sun), (TBD) (Fig. 3.2-2).
A second constraint is the yaw angle defined as the rotation around the Zs-axis being
zero when the sun is in the Xs-Ys plane. This roll angle shall be limited to +/- 2 deg,
(TBD).
Any additional (temporary) constraints, e.g., spacecraft-moon angles, are TBD.
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Zs
5 deg (no margin)
Xs
Ys
30 deg
Permissible sun
direction *1
*1 Angle between the sun direction
and Ys-axis along Zs-axis should be
within +-2 deg.
Fig.3.2-2 Aspect Angle Constraints (TBD)
3.2.2.2 FPC-G’s FOV constraints
Constraints for step angle are 3’x3’about Xs, Ys-axis based on FOV of FPC-G. And for
the same reason, other poiniting performance shall be specified if the angle which
equals scan speed times scan duration time is over FOV of FPC-G.
3.2.3 Pointing Control Modes
[Assumption Conditions]
(1) More than two FPI operations are not performed at the same time.
(2) Observation duration of each FPI is from a few days to a week.
(3) Observation operation is fundamentally an on-board automatic operation based on
the operation plan uploaded from the ground, we do not perform real time operations
from the ground.
3.2.3.1 Definitions of Modes
Definition of operation mode in each observation mode are described in Table 3.2-1.
And AOCS operation mode and mode transition are shown in Fig. 3.2-3.
Table 3.2-1 Definition of operation mode in each observation mode
Operation Mode
Pointing Mode
Step Mode
Definition
This is a mode to observe fixed stars against
the inertial frame. It is achieved by pointing
the telescope boresight toward the
apparent star.
This is a mode for moving from an arbitrary
pointing direction to the next adjacent
direction. We do not perform observations
while moving the pointing direction. After
Remarks
This mode requires aberration
correction about the direction of
apparent star.
This mode is designed for attitude
maneuvers up to a few arcmin.
This sequence of motion is
repeated as many times as
DOC. No. : JAXA-SPICA-SYS-ICS-0002
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attitude maneuvering and attitude settling,
the next pointing observation starts.
This is a mode to observe a comet. It is
achieved by pointing the telescope direction
to the apparent star.
This is a mode to observe a star by scanning
the pointing direction with constant speed
and direction against the inertial frame. It is
achieved by pointing the telescope direction
to time varying apparent target direction.
This is a mode to change the pointing
direction. We do not observe through attitude
maneuvers. We adjust the mission system
and spacecraft system for the preparation of
the subsequent pointing observation.
This is a mode to downlink data to ground
systems by attitude maneuver and pointing
HGA to the ground, in case of breakdown of
the driver system of X band HGA. We do not
observe in this mode.
This is a mode to adjust the focus in the focal
plane by driving the telescope’s secondary
mirror. This mode is operating in the initial
checkout phase.
This is a mode for searching a target stars by
raster scanning the FOV. This mode
corrects relatively large alignment error in
the initial checkout phase, in case
unexpected alignment shift occurs.
Non-sidereal Tracking
Mode
Slow-scan Mode
Attitude Maneuver
Mode
Down-link Operation
of Observation Data
Telescope Focus
Adjustment Mode
Raster Scan Mode
(TBD)
Separation
necessary.
This mode requires correction of
parallax and aberration about the
direction of apparent star.
This mode requires aberration
correction about the direction of
apparent star.
Attitude Maneuver
Safe Attitude (Canonical Attitude)
rate damping
Sun Acquisition
of Y-axis direction
RCS unloading
Anomaly 2
Initial attitude
acquisition
Normal Attitude
Control
Orbit Control
AOCS Pointing
Attitude acquisition about the Y-axis
FPC-G Pointing
Coronagraph Pointing
Deployment of Solar Array Paddle
Pointing
PR
Attitude ReAcquisition
Anomaly 1
Step
Sun Acquisition
of Y-axis direction
Pointing
Non-sidereal Tracking
Slow-scan
Attitude acquisition about Y-axis
Run-up of RW
Event
Thruster Control Mode
RW Control Mode
Non-sidereal Tracking
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Fig.3.2-3 AOCS operation mode and mode transition
3.2.3.2 Pointing Mode Requirements
Pointing accuracy requirements in each observation mode are described in Table. 3.2-2.
Table 3.2-2 Pointing accuracy requirements in each observation mode
Observation mode
MIR camera (Ch1) imaging-mode
MIR camera (Ch2) imaging-mode
MIR camera (Ch3) imaging-mode
MIR camera (Ch4) imaging-mode
MIR camera (Ch1)
spectroscopic-mode
MIR camera (Ch2)
spectroscopic-mode
MIR camera (Ch3)
spectroscopic-mode
MIR camera (Ch4)
spectroscopic-mode
MIR spectrometer (HIRES
S-mode)
MIR spectrometer (HIRES
L-mode)
MIR spectrometer (LWS
Arm-Short)
MIR spectrometer (LWS
Arm-Long)
SAFARI （SPECObserve Mode）
SAFARI（PHTObserve Mode）
BLISS dispersion
Absolute pointing control
accuracy [arcsec]
Axis of rotation
X, Y
Z
18 (3σ)
18 (3σ)
18 (3σ)
18 (3σ)
18 (3σ)
18 (3σ)
18 (3σ)
18 (3σ)
Pointing stability [arcsec](0-P)
/time
Axis of rotation
X, Y
Z
0.075 / 200[sec] 0.075 / 200[sec]
0.12 / 200[sec]
0.12 / 200[sec]
0.21 / 200[sec]
0.21 / 200[sec]
0.39 / 60[sec]
0.39 / 60[sec]
0.135 (3σ)
0.135 (3σ)
0.135 / 200[sec]
0.135 / 200[sec]
0.22 (3σ)
0.22 (3σ)
0.225 / 200[sec]
0.225 / 200[sec]
0.405 (3σ)
0.405 (3σ)
0.405 / 200[sec]
0.405 / 200[sec]
0.57 (3σ)
0.57 (3σ)
0.57 / 200[sec]
0.57 / 200[sec]
0.72 (3σ)
0.72 (3σ)
0.18 / 1000[sec]
0.18 / 1000[sec]
1.20 (3σ)
1.20 (3σ)
0.30 / 1000[sec]
0.30 / 1000[sec]
1.11 (3σ)
1.11 (3σ)
0.28 / 1000[sec]
0.28 / 1000[sec]
2.28 (3σ)
2.28 (3σ)
0.57 / 1000[sec]
0.57 / 1000[sec]
described in [AD-1].
described in [AD-1].
described in [AD-2].
Pointing accuracy requirements in pointing mode are described in Table. 3.2-3. Pointin
control accuracy is specified based on MIR camera (Ch1) spectroscopic-mode. And pointing
stability is specified based on MIR camera (Ch1) imaging-mode.
Table 3.2-3 Pointing accuracy requirements in pointing mode
Requirements
Pointing control accuracy
Pointing stability
Performance
Axis of rotation
X, Y
Z
0.135[arcsec]
0.135[arcsec]
(3σ)
(3σ)
0.075[arcsec]
0.075[arcsec]
(0-P)/200sec
(0-P)/200sec
Remarks
Dispersion requirement from MIR
camera
Imaging requirement from MIR
camera
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3.2.3.3 Step Mode Requirements
Pointing requirements in step mode are described in Table. 3.2-4. The settling time
determines as described in section 3.2.1.1. Step mode direction is about Xs-axis, Ys-axis
or combination with Xs and Ys-axis. step mode direction about Zs-axis shall not be
operated because of the aspect angle constraints described in section 3.2.2. Step mode
operation shall be planned considering the sun angle constraints.
Table 3.2-4 Pointing accuracy requirements in step mode
Observation mode
MIR camera
(Ch1)imaging-mode
MIR camera
(Ch2)imaging-mode
MIR camera
(Ch3)imaging-mode
MIR camera
(Ch4)imaging-mode
MIR camera
(Ch1)spectroscopic-mode
MIR camera
(Ch2)spectroscopic-mode
MIR camera
(Ch3)spectroscopic-mode
MIR camera
(Ch4)spectroscopic-mode
MIR spectrometer
(HIRES S-mode)
MIR spectrometer
(HIRES L-mode)
MIR spectrometer (LWS
Arm-Short)
MIR spectrometer (LWS
Arm-Long)
SAFARI（SPECObserve
Mode）
SAFARI（PHTObserve
Mode）
BLISS
Step angle
[arcsec]
Step angle
accuracy [arcsec]
Step direction
(Defined as 2 dof
about FOV
direction)
Pointing settling
time after Step
within [sec]
0.075-5.4
0.075
arbitrarily
100
0.12-9.0
0.12
arbitrarily
100
0.21-16.2
0.21
arbitrarily
100
0.39-22.8
0.39
arbitrarily
30
0.135-0.27
0.135
arbitrarily
100
0.225-0.45
0.225
arbitrarily
100
0.405-0.81
0.405
arbitrarily
100
0.57-1.14
0.57
arbitrarily
100
0.18-1.75
0.18
arbitrarily
500
0.30-3.0
0.3
arbitrarily
500
0.28-2.75
0.28
arbitrarily
500
0.57-5.4
0.57
arbitrarily
500
described in [AD-1].
described in [AD-1].
described in [AD-2].
3.2.3.4 Non-sidereal Tracking Mode Requirements
Pointing requirements in non-sidereal tracking mode are described in Table. 3.2-5.
These pointing requirements are bascally equivalent to those in pointing mode except
for observation mode has not non-sidereal tracking mode. And additional required
pointing performance about this mode are described in Table 3.2-6.
DOC. No. : JAXA-SPICA-SYS-ICS-0002
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Table 3.2-5 Pointing accuracy requirements in non-sidereal tracking mode
Observation mode
MIR spectrometer (HIRES
S-mode)
MIR spectrometer (HIRES
L-mode)
MIR spectrometer (LWS
Arm-Short)
MIR spectrometer (LWS
Arm-Long)
MIR camera (Ch1) imaging
MIR camera (Ch2) imaging
MIR camera (Ch3) imaging
MIR camera (Ch4) imaging
MIR camera (Ch1) dispersion
MIR camera (Ch2) dispersion
MIR camera (Ch3) dispersion
MIR camera (Ch4) dispersion
SAFARI （SPECObserve Mode）
SAFARI（PHTObserve Mode）
BLISS
Absolute pointing control
accuracy [arcsec]
Pointing stability [arcsec](0-P)
/time
0.72 (3σ)
0.18 / 1000[sec]
1.20 (3σ)
0.30 / 1000[sec]
1.11 (3σ)
0.28 / 1000[sec]
2.28 (3σ)
0.57 / 1000[sec]
18 (3σ)
18 (3σ)
18 (3σ)
18 (3σ)
0.135 (3σ)
0.22 (3σ)
0.405 (3σ)
0.57 (3σ)
0.075 / 200[sec]
0.12 / 200[sec]
0.21 / 200[sec]
0.39 / 200[sec]
0.135 / 200[sec]
0.225 / 200[sec]
0.405 / 200[sec]
0.57 / 200[sec]
described in [AD-1].
described in [AD-1].
described in [AD-2].
Table 3.2-6 Tracking performance requirements in non-sidereal tracking mode
Observation mode
MIR camera (Ch1) imaging
MIR camera (Ch2) imaging
MIR camera (Ch3) imaging
MIR camera (Ch4) imaging
MIR camera (Ch1) dispersion
MIR camera (Ch2) dispersion
MIR camera (Ch3) dispersion
MIR camera (Ch4) dispersion
MIR spectrometer (HIRES
S-mode)
MIR spectrometer (HIRES
L-mode)
MIR spectrometer (LWS
Arm-Short)
MIR spectrometer (LWS
Arm-Long)
SAFARI （SPECObserve Mode）
SAFARI（PHTObserve Mode）
BLISS
Tracking speed range [arcsec/sec]
0.1667(=10[arcsec/min])
0.1667(=10[arcsec/min])
0.1667(=10[arcsec/min])
0.1667(=10[arcsec/min])
0.1667(=10[arcsec/min])
0.1667(=10[arcsec/min])
0.1667(=10[arcsec/min])
0.1667(=10[arcsec/min])
0.1667(=10[arcsec/min])
Tracking duration [sec]
1200[sec]
1200[sec]
1200[sec]
1200[sec]
1200[sec]
1200[sec]
1200[sec]
1200[sec]
0.1667(=10[arcsec/min])
0.1667(=10[arcsec/min])
0.1667(=10[arcsec/min])
1200[sec]
1200[sec]
1200[sec]
1200[sec]
described in [AD-1].
described in [AD-1].
described in [AD-2].
Remark: The pointing accuracy requirement similar to pointing mode are stringent
because of following reason;
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :17
- target direction model error
- mosaic error which is induced when guide star is moving in FOV of FPC-G
Therefore pointing accuracy requirements need to be reconsidered with total pointing
performance including such a FPC-G error factors under the operational conditions.
3.2.3.5 Slow Scan Mode Requirements
Pointing requirements in slow-scan mode are described in Table. 3.2-7. If the angle
which equals scan speed times scan duration time is over FOV of FPC-G, other
poiniting performance shall be specified as described in section 3.2.2.2.
Table 3.2-7 Pointing accuracy requirements in slow scan mode
Observation mode
MIR camera (Ch1)
imaging
MIR camera (Ch2)
imaging
MIR camera (Ch3)
imaging
MIR camera (Ch4)
imaging
MIR camera (Ch1)
dispersion
MIR camera (Ch2)
dispersion
MIR camera (Ch3)
dispersion
MIR camera (Ch4)
dispersion
MIR spectrometer
(HIRES S-mode)
MIR spectrometer
(HIRES L-mode)
MIR spectrometer (LWS
Arm-Short)
MIR spectrometer (LWS
Arm-Long)
SAFARI （SPECObserve
Mode）
SAFARI（PHTObserve
Mode）
BLISS
Scan speed range
[arcsec/sec]
Scan speed accuracy
[arcsec/sec]
N/A
N/A
N/A
N/A
N/A
N/A
N/A
N/A
0.054-0.54
0.005-0.054
5-50 or more
0.09-0.90
0.009-0.09
5-50 or more
0.162-1.62
0.0162-0.162
5-50 or more
0.228-2.28
0.0228-0.228
5-50 or more
TBD
TBD
TBD
TBD
described in [AD-1].
described in [AD-1].
described in [AD-2].
3.2.3.6 Coronagraph Mode Requirements
3.2.3.6.1 Pointing Mode Requirements
Scan duration [sec]
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :18
Pointing accuracy requirements in coronagraph pointing mode (using C-FPC/C-TTM)
are described in Table. 3.2-8.
Table 3.2-8 Pointing accuracy requirements in coronagraph pointing mode
Requirements
Pointing control accuracy
Pointing stability
Performance
0.03 [arcsec](3σ)
0.03 [arcsec](0-P)/20min
Remarks
3.2.3.6.2 Step Mode requirements
Pointing accuracy requirements in coronagraph step mode (using C-FPC/C-TTM) are
described in Table. 3.2-9. The settling time determines as described in section 3.2.1.1.
Step mode direction is about Xs-axis, Ys-axis or combination with Xs and Ys-axis. step
mode direction about Zs-axis shall not be operated because of the aspect angle
constraints described in section 3.2.2. Step mode operation shall be planned
considering the sun angle constraints.
Table 3.2-9 Pointing accuracy requirements in coronagraph step mode
Observation mode
Step angle [arcsec]
Step angle
accuracy [arcsec]
Step direction
(Defined as 2 dof
about FOV
direction)
Pointing settling
time after Step
within [sec]
N/A
N/A
N/A
N/A
Coronagraph
observation
instruments
3.2.3.6.3 Non-sidereal Tracking Mode requirements
Pointing accuracy requirements in coronagraph non-sidereal tracking mode (using
C-FPC/C-TTM) are described in Table. 3.2-10. And additional required pointing
performance about this mode are described in Table 3.2-11.
Table 3.2-10 Pointing accuracy requirements in coronagraph non-sidereal tracking mode
Observation mode
Coronagraph observation
instruments
Absolute pointing control
accuracy [arcsec]
Pointing stability [arcsec](0-P)
/time
N/A
N/A
Table 3.2-11 Tracking performance requirements in coronagraph non-sidereal tracking
mode
Observation mode
Coronagraph observation
instruments
Tracking speed range [arcsec/sec]
N/A
3.2.3.6.4 Slow Scan Mode requirements
Tracking duration [sec]
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :19
Tracking performance requirements in coronagraph slow scan mode are described in
Table. 3.2-12. If the angle which equals scan speed times scan duration time is over FOV
of FPC-G, other poiniting performance shall be specified as described in section 3.2.2.2.
Table 3.2-12 Pointing accuracy requirements in coronagraph slow scan mode
Observation mode
Scan speed range
[arcsec/sec]
Scan speed accuracy
[arcsec/sec]
Coronagraph
observation instruments
N/A
N/A
Scan duration [sec]
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :20
4．FPIA Mechanical Interface Requirements
4.1
Overview
FPIs shall have mechanical interface at the Instrument Optical Bench (IOB) attached
to STA through three kinetic mounts. IOB is the basic mechanical structural
component of FPIA, made of (tentatively) aluminum. Here we define IOBA (IOB
assembly) consisting of the IOB, a common pick of module (PoM) for providing
telescope optical beams to the FPI entrance apertures, kinetic mounts (bipods)
supporting FPIA, electric connector port, and the 6K shield protecting FPIs from
stray light.
The volume occupied by all FPIs is strictly limited to within a column of
2.3m diameter, 0.40m in height. The total mass of the whole FPIA must be within
200kg with 20% margin.
Fig.4-1 IOB and the FPI volume
4.2 Coordinate system
4.2.1 Spacecraft Coordinate System
The spacecraft coordinate system (shown in Fig. 4.2-1 ) is a right-handed, orthogonal
coordinate system, defined as follows:
• The origin, Os, is located at the center of the satellite/launch-vehicle
separation plane (TBC).
• The Xs axis completes the right-handed, orthogonal coordinate system.
• The Ys axis coincides with the line pointing positively towards the sun.
• The Zs axis is aligned with the launch vehicle thrust axis, pointing positively
from the interface plane towards the spacecraft.
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :21
Fig. 4.2-1 The spacecraft coordinate system
4.2.2 Spacecraft Body Coordinate System
The spacecraft coordinate system (shown in Fig. 4.2-2 ) is a right-handed, orthogonal
coordinate system, defined as follows:
• The origin, OB, is located at the center of gravity.
• The XB axis is parallel to Xs axis.
• The YB axis is parallel to Ys axis.
• The ZB axis is parallel to Zs axis.
Fig. 4.2-2 The spacecraft body coordinate system
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :22
4.2.3 IOB Coordinate System
The IOB coordinate system is a right-handed, orthogonal coordinate system, defined as
follows:
• The origin, OIOB, is located at the IOB geometric center.
• The XIOB axis completes the right-handed, orthogonal coordinate system..
• The YB axis is in IOB plane and projection of nominal YB -axis to IOB plane.
• The ZB axis is perpendicular to IOB plane.
4.2.4 FPI Coordinate System
(Each FPI coordinate system shall be described.)
4.2.5 FPC-G Coordinate System
The FPC-G coordinate system (or called reference frame) is identical to the Satellite
body coordinate system when the AOCS sensors alignment error are assumed to be
zero.
4.3 Cold Volume, Mass requirement from FPIs
FPI
Weight
(kg)
comment
MIRACLE
MIRMES
60.0
MIRHES
with 20% margin
SCI
30.0
FPC
10.0
SAFARI
50.0
BLISS
30.0
(optional FPI)
IOB, FPI cover
50.0
with 20% margin
Total
200
excluding BLISS
Table 4.2-1 Cold instrument mass requested
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :23
Cold instrumental volume, and their mass requested from FPIs are summarized in
Table 4.2-1 & 4.2-2.
FPI
Volume(cm3)
MIRACLE (Ch 1, 3)
200000
MIRACLE (Ch 2, 4)
200000
MIR moderate resolution
Spectrometer (ARM-L)
200000
MIR moderate resolution
Spectrometer (ARM-S)
200000
MIR High-dispersion
Spectrometer (LW)
24500
MIR High-dispersion
Spectrometer (SW)
24500
MIR Coronagraph
FPC
552233
39000
SAFARI
BLISS
IOB, FPI cover
Total (above IOB)
comment
each
35x35x20
each
90% of r=125,
30x26x50
174138
93x51.3x36.5
70000
50x35x40
219800
IOB : 200cm dia. 7cm thick
1684370
86%
Table 4.2-2. Cold instrumental volume requirement.
4.3 Mass property
The total mass of FPIA (including the IOB) shall not exceed 200 kg (with 20% margin).
The 1st lateral eigenfrequency requirement is >50Hz in any axis. IOB is tentatively
considered as 200cm diameter, 7cm thick ribbed plate made of Aluminum (other
material is also considered).
The estimated eigenfrequencies are summarized in Table 4.3-1 (the definition of axis is
given in JAXA-SPICA-IF0001). FPI center of gravity, moment of inertia shall be shown
in Table 4.3-2 and 4.3-3.
Table 4.3-1 FPI(incl. IOB) 1st eigen frequencies (Tentative)
Instrument
Mass
X
Y
Z
(kg)
IOB alone
50
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :24
Whole FPI + IOB
X
TBD
< 200
Table 4.3-2 FPI Center of gravity
Y
Z
TBD
TBD
Table 4.3-3 FPI Mass property
MOI (kg･mm2)
MOP (kg･mm2)
Ixx
Iyy
Izz
Jxy
Jyz
Jzx
TBD
TBD
TBD
TBD
TBD
TBD
4.4. FPIA configuration
Configuration of the FPIA (cold-hardware of FPIs on IOB) in the allowed FPI volume
(Fig.4-1) is shown in Fig. 4-2.
.
Fig.4-2 FPI configuration viewed from “Top (telescope side)”
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :25
4.5 Disturbance Management
4.6.1 Disturbance Source in FPIA
4.6.2 Disturbance Susceptibility
4.6
Mounting Conditions
TBD.
4.7
Alignment
Attaching surface of the FPIs on the IOB shall be the reference surface for alignment
of each FPI.
Details are TBD.
FPI and the FPC-G reference frame shall be co-aligned.
The misalignment, i.e., the angle between the optical axes of FPI and the FPC-G
reference frame, shall be very small compared to the FoV of the instrument.
4.8 Surface Treatment and Surface Roughness
TBD
4.9
FPI Handling, Installation
Tbd, responsibility, access point etc.
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :26
5．FPIA Thermal Interface
5.1
Overview
Thermal conductive interface between the FPI assembly and CRYO shall be defined
by the temperature of the heat strap attached to the cold finger of one of mechanical
coolers of the CRYO as shown in Figure 5.1-1.
Fig.5.1-1 Thermal connections in SPICA
FPI is radiatively coupled with the baffle and the bottom part of telescope shell.
The schematic diagram of the thermal interface between FPI and CRYO is shown in
Figure 5.1-2.
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :27
FPI is required to equip heat switches to disconnect itself from the cooling chain to
avoid thermal short in case of unexpected failure of FPI or coolers at each connecting
point to heat strap from coolers.(TBD)
Fig.5.1-2 The schematic diagram of the thermal interface between FPI and CRYO
5.2
Heat generation and thermal lift requirements
Total maximum heat dissipation in FPI assembly shall be less than 15mW @ 4.5K
stage and 5mW @1.7K stage.
Temporary maximum heat dissipation shall be less than TBD mW x TBD minutes.
Heat dissipation / thermal lift requirements are summarized in Table 5.2-1~5.2-4.
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :28
Total Maximum load@1.7K
obs. Mode
MIRACLE
MIRMES
MIRHES
SCI
FPC-S
SAFARI
BLISS
MIRACLE
2.28
0.28
0.28
0.28
0.28
0.28
0.28
MIRMES
0.14
1
0.14
0.14
0.14
0.14
0.14
includes all loads from all the FPIs.
load from each FPI
MIRHES SCI
FPC-S
FPC-G
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
SAFARI
2
2
2
2
2
5.7
2
unit : mW
BLISS
2.1
2.1
2.1
2.1
2.1
2.1
2.7
Total Average load@1.7K
obs. Mode
MIRACLE
MIRMES
MIRHES
SCI
FPC-S
SAFARI
BLISS
MIRACLE
2.28
0.28
0.28
0.28
0.28
0.28
0.28
MIRMES
0.14
1
0.14
0.14
0.14
0.14
0.14
total
6.52
5.38
4.52
4.52
4.52
8.22
5.12
unit : mW
load from each FPI
MIRHES SCI
FPC-S
FPC-G
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
SAFARI
2
2
2
2
2
3.9
2
BLISS
2.1
2.1
2.1
2.1
2.1
2.1
2.5
total
6.52
5.38
4.52
4.52
4.52
6.42
4.92
Table 5.2-1 Total maximum load (top) / average load (bottom) at 1.7K stage
unit :
mW
Total Maximum load@4.5K
obs. Mode
MIRACLE
MIRMES
MIRHES
SCI
FPC-S
SAFARI
BLISS
MIRACLE
2.28
0.28
0.28
0.28
0.28
0.28
0.28
MIRMES
0.14
1
0.14
0.14
0.14
0.14
0.14
load from each FPI
MIRHES
SCI
FPC-S
0.28
0.56
0.1
0.28
0.56
0.1
2
0.56
0.1
0.28
10.56
0.1
0.28
0.56
2
0.28
0.56
0.1
0.28
0.56
0.1
FPC-G
2
2
2
2
2
2
2
SAFARI
3
3
3
3
3
13
3
BLISS
0
0
0
0
0
0
0
MIRACLE
MIRMES
MIRHES
SCI
FPC-S
SAFARI
BLISS
MIRACLE
2.28
0.28
0.28
0.28
0.28
0.28
0.28
MIRMES
0.14
1
0.14
0.14
0.14
0.14
0.14
8.36
7.22
8.08
16.36
8.26
16.36
6.36
unit :
mW
Total Average load@4.5K
obs. Mode
total
load from each FPI
MIRHES
SCI
FPC-S
0.28
0.56
0.1
0.28
0.56
0.1
2
0.56
0.1
0.28
10.56
0.1
0.28
0.56
2
0.28
0.56
0.1
0.28
0.56
0.1
FPC-G
2
2
2
2
2
2
2
SAFARI
3
3
3
3
3
9.7
3
BLISS
0
0
0
0
0
0
0
Table 5.2-2 Total maximum load (top) / average load (bottom) at 4.5K stage
total
8.36
7.22
8.08
16.36
8.26
13.06
6.36
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :29
MIRACLE
unit
Requirement
Parasitic
Active Total
Remarks
1.7K J-T stage
1.7 K
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
mK
mW
mW
<3
100
0.28
0.28
2
2
2.28
2.28
4.5K J-T stage
4.5 K
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
mK
mW
mW
<6
100
0.28
0.28
2
2
2.28
2.28
Si:Sb x2, assume 1 m to
12K stage with 7 core
CMN (Manganin) wiring
Si:As x 2, assume 1 m to
12 K stage with 7 core
CMN
peak =
average(neglecting filter
wheel)
18K 2ST stage
18K
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
K
mW
mW
6.6
<20
1
11.2
17.8
Lift required at shield 1-3(45-95K)
45 K
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
K
mW
mW
65 K
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
K
mW
mW
temperature stability requirement
Average lift
Peak lift
description of thermal event/profile
during the FPI operation (in free format)
parasitic : instrument
off
active : ON, excl.
parasitic
95 K
temperature of stage
temperature range requirement
Buffer for Si:Sb x 2 +
Si:As x 2, assume 10 m
to 300 K stage with 7
core CMN
Dissipation from filter
wheel mortion is
neglected
Dissipation in the
annealing mode is TBD
K
K
mW
mW
put link information for the figure
Table 5.2-3 Heat dissipation / lift requirements (MIRACLE)
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :30
SCI
unit
1.7K J-T stage
temperature of stage
temperature range
requirement
temperature stability
requirement
Average lift
Peak lift
4.5K J-T stage
temperature of stage
temperature range
requirement
temperature stability
requirement
Average lift
Peak lift
18K 2ST stage
temperature of stage
temperature range
requirement
temperature stability
requirement
Average lift
Peak lift
Lift required at shield 1-3(45-95K)
temperature of stage
temperature range
requirement
temperature stability
requirement
Average lift
Peak lift
temperature of stage
temperature range
requirement
temperature stability
requirement
Average lift
Peak lift
temperature of stage
temperature range
requirement
temperature stability
requirement
Average lift
Peak lift
description of thermal event/profile
during the FPI operation (in free
format)
Requirement
Parasitic Active Total
Remarks
1.7 K
K
mK
mW
mW
not applicable
4.5 K
K
mK
mW
mW
0.56
0.56
10
10
10.56
10.56
parasitic assumes 1/2 of SHI
1000 wire-harness
18K
K
K
mW
mW
not applicable?
45 K
K
K
mW
mW
K
K
mW
mW
K
K
mW
mW
110.0
110.0
65 K
0.0
0.0
110.0
110.0
parasitic assumes 1/2 of
SHI 1000 wire-harness
237
237
95 K
0
0
237
237
225
225
0
0
225
225
put link information for the figure
Table 5.2-4 Heat dissipation / lift requirements (SCI)
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :31
SAFARI
unit
Requirement
parasitic
Active Total
Remarks
1.7K J-T stage
K
mK
mW
mW
1.7 K
TBD
TBD
2
1.9
2
3.7
3.9
5.7
K
mK
mW
mW
4.5 K
TBD
TBD
3
6.7
3
10
9.7
13
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
NEED reconsideration
for NO 2.5K stage design
4.5K J-T stage
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
"active": 8mW w/o margin
12K 2ST stage
12K
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
K
mW
mW
0.0
0.0
13.3
30.0
13.3
30
originally estimated for
20K
stage, so the worst case
Lift required at shield 1-3(45-95K)
45 K
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
K
mW
mW
65 K
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
K
mW
mW
95 K
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
description of thermal event/profile
during the FPI operation (in free format)
K
K
mW
mW
parasitic : instrument off
active : ON, excl.
parasitic
See Fig. 5.2-9
Table 5.2-5 Hear generation / lift requirements (SAFARI)
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :32
BLISS
unit
Requirement
parasitic Active Total
Remarks
1.7K J-T stage
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
mK
mW
mW
1.7 K
1.6-1.8 K
100 mK
2.1
0.4
2.1
0.6
for the BLISS ADR.
not a strong constraint
2.5
2.7
4.5K J-T stage
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
mK
mW
mW
4.5 K
1.6-1.8 K
100 mK
1.1mW Parasitic from
ADR wires only
for Housing
modest
very small
12K 2ST stage
12K
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
K
mW
mW
3.8
3.8
<14
1K
5.9
5.9
9.7
9.7
Lift required at shield 1-3(45-95K)
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
K
mW
mW
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
K
mW
mW
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
description of thermal event/profile
during the FPI operation (in free format)
K
K
mW
mW
45 K
40-50
2 (0-p) per hour
3.7
1.3
5.0
3.7
1.3
5.0
65 K
60-70 K
3 (0-p) per hour
19.7
53.3
73
19.7
217
236.7
95 K
90-100 K
4 (0-p) per hour
69.7
226
295.7
69.7
835
904.7
We are assuming heat
sinking at all intercept
points, since this
minimizes the total
heat load to lower
temperatures. Thermal
system not sensitive to
this temp.
Numbers do not
include any margin.
A conservative margin
to apply would be 50%
See Fig. 5.2-10
Table 5.2-6 Hear generation / lift requirements (BLISS)
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :33
MIRMES
1.7K J-T stage
temperature of stage
temperature range
requirement
temperature stability
requirement
Average lift
Peak lift
4.5K J-T stage
temperature of stage
temperature range
requirement
temperature stability
requirement
Average lift
Peak lift
12K 2ST stage
temperature of stage
temperature range
requirement
temperature stability
requirement
Average lift
Peak lift
MIRHES
1.7K J-T stage
temperature of stage
temperature range
requirement
temperature stability
requirement
Average lift
Peak lift
4.5K J-T stage
temperature of stage
temperature range
requirement
temperature stability
requirement
Average lift
Peak lift
12K 2ST stage
temperature of stage
temperature range
requirement
temperature stability
requirement
Average lift
Peak lift
unit
Requirement
parasitic
Active Total
parasitic : instrument off
active : ON, incl. parasitic
1.7 K
K
mK
mW
mW
0.0
0.0
K
mK
mW
mW
4.5 K
5.0K
100mK
0.0
1.0
0.0
1.0
3K
100mK
1.0
1.0
1.0
1.0
1.0
1.0
unit
Requirement
parasitic
Active Total
1.7 K
not applicable
4.5 K
5.0K
100mK
0.0
2.0
0.0
2.0
12K
K
K
mW
mW
Remarks
parasitic : instrument off
active : ON, incl. parasitic
K
mK
mW
mW
K
mK
mW
mW
Si:As 1kX1K x 1
Low temp to reduce dark
Heat sink for wire
Pre-Amp at low temp.
stage
20K
1K
50.0
50.0
1.0
1.0
Temp. at detector
Si:Sb 1kX1K x 1
Low temp to reduce
dark
Temp. at detector
12K
K
K
mW
mW
Remarks
1.0
1.0
20K
1K
50.0
50.0
Temp. at detector
2.0
2.0
Si:As 1kX1K x 2
Low temp to reduce dark
Heat sink for wire
Pre-Amp at low temp.
stage
Table 5.2-7 Hear generation / lift requirements (MIRMES/MIRHES)
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :34
FPC-G
unit
Requirement
Parasitic
Active Total
Remarks
1.7K J-T stage
1.7 K
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
mK
mW
mW
not applicable
4.5K J-T stage
4.5 K
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
FPC-S
K
mK
mW
mW
unit
NA
NA
0
0
2
2
2
2
Requirement
Parasitic
Active Total
based on AKARI/NIR,
parasitic should be
taken from MIRACLE?
Remarks
1.7K J-T stage
1.7 K
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
mK
mW
mW
not applicable
4.5K J-T stage
4.5 K
temperature of stage
temperature range requirement
temperature stability requirement
Average lift
Peak lift
K
mK
mW
mW
NA
NA
0
0
2
2
2
2
Table 5.2-8 Hear generation / lift requirements (FPC-S/FPC-G)
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :35
Fig. 5.2-9 estimated profile of the heat loads during SAFARI cooler cycle
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :36
Fig. 5.2-10 thermal profile of BLISS cooler in operation
5.3
Parasitic Heat from Harness
Harness for FPI shall be per table 5.3-1. (same as Table ????? in [AD-5] )
Table 5.3-1 FPI harness
Type of wire
Material
Diameter
(mm)
Length (m)
Twisted
pair for
general
signal
Shielded
line for
general
signal
Single
wire for
general
signal
Twisted
pair for
power line
Twisted
pair for
motor
power line
Shield
Manganin
SUS
0.1
0.1
0.1
0.2x2
0.5x2
Aluminize
d
Polyester
N/A
6
6
6
6
6
6
1,000
0
0
0
0
0
Mangani
Manganin Manganin
n
Number
Tota
l
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :37
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :38
6.
FPIA Optical Interface
6.1 Definitions
6.2 Field-of-view(FOV) configuration
Fig.6.1-1 Field-of-view sharing
6.3 Alignment Requirements
6.4 Aspect angle Constraints
TBD
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :39
7．Electrical Interface
7.1
Overview
Harness from STA interface connector to the electronics box shall be prepared by
CRYO team.
Electrical interface between the STA and the CRYO shall be STA interface connector.
Conceptual drawing of the electrical interface is shown in figure 7.1-1.
7.2
Interface Connectors, Wire Harness
Location and dimensions of FPI interface connectors are shown in figure TBD.
CRYO
FPI Control
Electronics
S/C’s
scope
FPI’s scope
FPI
CRYO’s scope
FPI’s scope
Fig. 7.1-1 Conceptual drawing of the electrical interface between CRYO and FPI
7.3
FPI control Electronics (Warm)
1) Volume, Mass
Mass with 20% margin of the warm electronics (excluding the harness) are listed in
Table 7.3-1.
their weights.
The volumes are tentatively scaled from AKARI FPI electronics, by
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :40
Function
Component
FPI
MIRACLE
MIRMES
MIRHES
SCI
FPC
SAFARI
BLISS
#. Pcs.
Focal-Plane Array
4
Filter wheel
2
Grism wheel
2
Slit-mask changer
2
Focal-Plane Array
2
Cold Shutter
2
Focal-Plane Array
2
Cold Shutter
2
Focal -Plane Array
(incl. T-T sensor)
4
Deformable mirror
driver
1
tip-tilt driver (Note1)
1
Mask changer
2
Focal-Plane Array
3
Filter wheel
1
Focal-Plane Array
3
3+4He & ADR
1
Filter wheel
2
Fourier-Transform
Mechanism
1
Focal-plane linear array
5
ADR
1
cold chopper
1
Total
Weight （kg）
Weight
(kg)
with 20% margin
Volume
[mm3]
11.3
13.6
400x300x280
6
7.2
400x300x150
6
7.2
400x300x150
21
25
400x500x200
8
10
400x300x200
24
29
ICU
W380xL330xH270
DCU
W380xL330xH270
23.7
28
400x600x300
100
120
---
Table 7.3-1 Mass & volume requirement of FPI warm electronics
2) Power, Heat-dissipation
Power consumption of the warm electronics and the power dissipation to the spacecraft
bus module are summarized in Table 7.3-2 and 7.3-3. The dissipation is assumed to be
100% of the power consumption. Note that the total power varies according to the
observation mode : the observations will be executed by using a single FPI except for the
focal-plane finding camera, FPC-G.
FPI
Function
Component
#.
Pcs.
Power
(W)
Power
Dissipation
Power
(W)
Power
Dissipation
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :41
[ Observing ]
MIRACLE
MIRMES
MIRHES
SCI
FPC
SAFARI
(Note 3)
BLISS
Focal-Plane Array
4
Filter wheel
2
Grism wheel
2
Slit-mask changer
2
Focal-Plane Array
2
Cold Shutter
2
Focal-Plane Array
2
Cold Shutter
2
Focal -Plane Array
(incl. T-T sensors)
Deformable mirror
driver
tip-tilt driver (Note1)
17
17
17
17
9
9
9
9
9
9
9
9
60
60
16
16
12
12
12
12
120
120
17
17
61
61
16
16
4
1
1
Mask changer
2
Focal-Plane Array
3
Filter wheel
1
Focal-Plane Array
3
3+4He & ADR
1
Filter wheel
2
Fourier-Transform
Mechanism
1
Focal-plane linear array
5
ADR
1
cold chopper
1
Total
[ Standby ]
Note 2
Table 7.3-2 Electric power & heat dissipation requirement of FPI warm electronics
Note 1: high-vol. (400V) is necessary for Piezo drives.
Note 2 : Powers(& dissipations) are the target values, no margin is included. Also note
that only a single FPI (except for FPC-G) will be used for observation.
Note 3: SAFARI warm electronics consists of two units: ICU and DCU.
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :42
Obs. (Ave.)
Obs.(Max.)
Standby
MIRACLE
17
17
17
MIRMES
9
9
9
"Standby" is defined to be the mode during the observation by other FPI.
Assume MAX=average (update
unit : W
later)
MIRHES SCI FPC-S FPC-G
SAFARI
BLISS
9
60
4
8
120
61
9
60
4
8
120
61
9
16
4
8
17
16
summary of total Power
obs. Mode
MIRACLE
MIRMES
MIRHES
SCI
FPC-S
SAFARI
BLISS
MIRACLE
17
17
17
17
17
17
17
MIRMES
9
9
9
9
9
9
9
unit : W
Power required for each FPI
MIRHES SCI FPC-S FPC-G
9
16
4
8
9
16
4
8
9
16
4
8
9
60
4
8
9
16
4
8
9
16
4
8
9
16
4
8
SAFARI
17
17
17
17
17
120
17
BLISS
16
16
16
16
16
16
61
total
96
96
96
140
96
199
141
Table 7.3-3 FPI Electronics power variation according to the observation mode
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :43
7.4. SCI-AOCS I/F
TBD.
8. Onboard Data Handling Interface
8.1 Definitions
8.2 Command Interface
8.3 Telemetry Interface
9. Dynamical Interface
9.1 Definitions
9.2 Flexibility Parameters
10. FPIA Development and Verification
10.1 Overview
FPIA development and verification plan can be divided to the individual FPI level and the
system level.
In the individual FPI level, following tests shall be defined and addressed in each FPI
development and test plan:
(1) Item 1
(2) Item 2
(3) etc etc…
The system-level test plan should take account of the critical issues as below:
(a) FPI is cooled to <5K with J-T coolers under extremely careful Spacecraft thermal
design.
(b) disturbance and interference from J-T coolers and AOCS (such as RW, gyro) in
order to assure high-sensitivity (low-noise) in orbit
(c) Co-operation with FPC-G to establish the pointing stability: interferences?
alignment?
(d) Co-focus among FPIs (especially MIR’s) since STA 2ry cannot be adjusted so
frequently in orbit
By taking account of the above issues, following tests shall be defined in the system level:
(a) With STM:
 Measure disturbance at FPI from J-T/AOCS under Spacecraft MTM test in 2014
(b) With CQM:
 Cooling test with J-T (PM) (in PLM (PM))
 Evaluate effect of mechanical disturbances from J-T/AOCS simulator, electrical
interferences among FPIs, J-T, AOCS in the latter half of FY2015
(c) With FM
 FPI evaluation at cold (optical & electrical)
 STA optical performance test at cold
 PLM thermal test
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :44
10.2 Model philosophy
Minimum number of Models required for the system level test (in the previous page) is:
FM (Flight Model) (& its spare)
STM : structure thermal model
CQM : cold qualification model
STM : Structure Thermal Model
Description:
 Mechanical I/F specifications (including disturbance sources) is equivalent to that
of FM
Required Function
 Same mechanical I/F specifications to FM
 Nearly the same thermal I/F (TBD, for spacecraft(PM) thermal test)
 Equipped with thermometers, acceleration sensors for measurement of I/F
environmental condition
 Simulate mechanical disturbance according to the system operation modes
CQM :Cold Qualification Model
Description
 Nearly equivalent to FM incorporating with detectors operable at
low-temperature expected in orbit
Required Function
 Same thermal, mechanical, electrical I/F specifications to FM
 Equipped with detectors operable at low-temperature, with the same noise
performance as that of FM
 Simulate heat-dissipation (load to J-Ts), mechanical disturbance according to the
system operation modes
10.3 Analyses
10.4 Testing
10.4.1 Overview
10.4.2 Electrical Functional Test Requirements
10.4.3 EMC Test Requirements
10.4.4 Structural Test Requirements for FPIA
(1) Stiffness
>100Hz
(2) Quasi-static load
25G each axis
(3) Sinusoidal vibration condition
5～100Hz
(4) Random Vibration
20G each axis
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :45
20～
80Hz
+6dB/oct
80～270Hz
0.7G2/Hz
270～413Hz
-6dB/oct
413～800Hz
0.3G2/Hz
800～2000Hz -8dB/oct
Overall 21.1Grms
duration
60sec
(5) Shock test level
100～1500Hz +8dB/oct
1500～4000Hz 500Gsrs
Q=10
(6) Acoustic test level
1/1 Octave
Sound pressure level
Center frequency (Hz)
(dB)
Tolerance (dB)
Duration
(sec)
0dB=2 x 10-5 Pa
31.5
128
+3/-10*1
63
129.5
+/- 3
125
134
+/- 3
250
136
+/- 3
500
131.5
+/- 3
1000
128
+/- 3
2000
123
+/- 3
4000
118
+3/-6
8000
116
+/- 6*1
Overall
140.5
+/- 2
*1: Depends on the capacity of the test facility
*2: QT level = AT level + 3 dB, Duration = 80 sec
11. Product Assurance
40
DOC. No. : JAXA-SPICA-SYS-ICS-0002
REV. : draft PAGE :46
12. Programme Requirements
Appendices