Transcript Mini-EUSO Schedule and documentation

Mini-EUSO Schedule and
documentation
Schedule
• 28/11-2/12/2016 FM Focal Surface integration, Paris.
• 5-9/12/2016 EM integrated tests, Rome.
• 12/12/2016-6/1/2016 FM integration (electronics, FM lenses),
calibration, functional tests, Tokyo
• 10-31/1/2017 FM final integration, Rome
• 1-28/2/2017 FM tests (inrush current, vibration, EM
compatibility, thermal vacuum, outgassing)
• 1/3/2017 Delivery of FM model to Russia (TBC)
• Documents mention 2018, but need to discuss with ASI
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The launch failure of Russia's
Progress MS-04 cargo spacecraft
was due to an emergency
shutdown of the third stage
engine, which occurred at the
same time as premature
separation between the third
stage and the spacecraft according
to Russia's Mission Control Center.
Resupply spacecraft, was lost 382
seconds after launch on
December 1, 2016
Briefly, the third stage and the
spacecraft separated, for
unknown reasons, 140 seconds
prematurely. The spacecraft
interpreted the separation as the
normal event that would occur
once it was in orbit and began
deploying its antennas and
preparing its attitude control
thrusters. The third stage was still
firing and bumped into the
spacecraft, sending it tumbling
and leading to catastrophic failure
of both.
Documentation
Document
Title
List of 200-xx
documents
for the Experiment «UV-Atmosphere (Mini-EUSO)» Document No.
Technical Specification for the Equipment (TS-EQ)
Logbook of Equipment
ххх-xxx-200
ххх-xxx-200PS
Technical Description (TD)
ххх-xxx-201
Operations Manual (OM)
ххх-xxx-202
Acceptance Test Programme (ATP)
ххх-xxx-203
ххх-xxx-204
ххх-xxx-205
Equipment Incoming Inspection Manual
Qualification Test Program
Qualification Test Reports and Certificate
Hazard / Safety Analyses ;
Safety Assessment Report
List of Non-metallic Materials/Declared Materials List
Specific Certificates (fire safety, toxicity, etc.)
ххх-xxx-206
ххх-xxx-207
ххх-xxx-207-01
ххх-xxx-207-02
ххх-xxx-207-11
Crew Procedures, Training and BDC Documentation
Control Test Equipment Documentation
Detailed Electrical Circuit Diagram (DECD)
General Electrical Circuit Diagram (GECD)
Outline Installation Drawings (OID)
ххх-xxx-208
ххх-xxx-209
ххх-xxx-210-01
ххх-xxx-210-02
ххх-xxx-211
№
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Actions
Issue of the Roscosmos Decision regarding order and organization of the activities for the scientific equipment
integration
The study of the issues regarding the scientific equipment integration for the experiment implementation, input
data exchange
(Venue – TBD)
Development and conformation of the 200-xx technical documentation for the equipment drafts according to
Appendix 4
(Venue – TBD)
Scientific equipment integration on-board of RS ISS, documentation development for mechanical and electrical
interfaces
Conformation of 200-xx Operating and Technical documentation
(Venue – TBD)
Qualification tests conduction of technological sample
(The place where it will be held – Rome, Italy)
Conformation of the qualification tests report, including security data
(Venue – TBD)
Delivery of Technological (training) sample of scientific equipment to RSC “Energia”
Production and tests of the mechanical and electrical interfaces in RSC “Energia”
Conduction of technological sample match mate tests with mechanical interface
(Venue – RSC “Energia”)
Crew training
(Venue – TBD)
Issue of the Flight Safety Certificate
AT-1of scientific equipment flight model
(Venue – Rome, Italy)
Delivery to RSC “Energia” of scientific equipment flight model
AT-2 of scientific equipment flight model (Venue – RSC “Energia”)
Delivery of the equipment to Baikonur, preflight preparation of the equipment with the participation of Italian
specialists
Thermal range
Operation Phase
Table 3
In production and storage facilities
Temperature
530 С
Transportation
50 С
Assembly and testing
040 С
At launch pad (for equipment)
040 С
Orbital flight (for unattended equipment)
040 С
Orbital flight (for cargoes when crew is present)
After descent module landing (for equipment)
1828 С*)
50 С
Offgassing
• 2.2.8.4. Requirements for Material
Offgassing
• Materials in the hardware installed on the ISS
exterior surfaces shall comply with standards
for vacuum offgassing specified as a mass loss
(not to exceed 1%) and condensable
substance amount (not to exceed 0.1%).
acceleration
• 3.2.2
In the injection phase
• Operating values of linear g-loads for cargoes
(with no allowance for the low-frequency
dynamic component) are:
• along the X-axis is +4.3,
• along the Y-,Z- axes is ±1.5.
Vibrations
• Vibration g-loads in 3 mutually perpendicular directions in the form of harmonic vibration are given in Table 5, and at frequencies more
than 20Hz in the form of random vibration are given in Table 6.
•
Table 5
The g-load change depending on a frequency change within the sub-band is linear.
For all vehicle
compartments
Flight Phases
Exposure duration,
seconds
Frequency sub-band, Hz
5-25
25-200
200-800
800-1500
1500-2500
Amplitude of vibration g-loads, g
Injection into Orbit
1
1-3
3-5
5-8
8
300
Table 6
The
change depending on a frequency change within the sub-band is linear.
Flightg-loadVehicle
Frequency sub-bands, Hz
Phases Compartmen
t
20-50
50-100
100-200
200-500
500-1000
Exposure
duration,
seconds
1000-2000
Spectral density of vibration acceleration, g2/Hz
HC, CC
0.02
0.02
0.02-0.05
0.05
0.05-0.025
0.025-0.013
120
DM
0.02
0.02
0.02
0.02
0.02-0.01
0.01-0.005
120
HM, CC, DM
0.02
0.02
0.02
0.02-
0.008-0.004
0.004-0.002
480
Injectio
n
into
orbit
0.008
•
Figure 12. Hardware Setup for Testing HF Interference Tolerance in Power Supply Circui
Power
Source
Equipment
Under Test
LISN
C
C
Test Signal
Generator
The instrument "ground" must be electrically
isolated from the LISN "ground"
Instrument
(spectrum analyzer,
oscilloscope
Hardware shall be powered by the ISS module
DC-power supply system (СЭП) source at a
nominal voltage of 28.50.5V at the СЭП
output terminals.
Power voltage supplied to the hardware inputs
in steady-state mode shall be in the 23-29V
range.
Test number and type
1. Check of cargo
completeness
2. Check of outward
appearance
3. Check of dimensions
4. Check of mass and position
of center of mass
5. Safety
6. Check of packaging
7. Vibrations during
transportation
8. Vibrations during insertion
9. Vibrations during landing of
Soyuz descent module
10. Vibrations in orbit
11. Shocks during insertion
12. Shocks during landing of
Soyuz vehicle descent module
13. Linear g-loads during
insertion
14. Linear g-loads during
landing of Soyuz descent
module
15. Humidity effects
16. Temperature during
transportation
17. Thermal cycle
18. Oxygen environment
19 Pressure
reduction/increase
20. Radiation conditions
21. Pressure integrity test
22. Isolation and breakdown
23.Starting current (23 V-28V32 V)
24. Working consumption (23
V - 28 V - 32 V)
25. Check of operating
properties, standalone tests
26.Eelectromagnetic
compatibility test
General
Requirements
Test
Requirements
2.1
Test Procedure
QM AT
FM AT
stages
stages
1
2
1
2
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2.2
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2.3.
2.4
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Х
Х
QT
2.6
2.5
2.7
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2.9
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2.7
2.7
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2.7
р
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р
2.8
2.9
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2.10
2.11
2.12
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2.16
2.18
2.19
2.19
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б/п
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Х
б/п
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2.19
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2.20
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2.14
х
Inrush current
• - start-up current rise or fall rate should not
exceed 0.125 A/мs;
• - if a current rate rise or fall rate is greater
than 0.125 A/мs, the resultant pulse energy
shall not exceed 0.1 A2 sec.
Insulation
•
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4.1.2. Insulation Electrical Resistance
The electrical resistance of the insulation between the primary power circuits
(both positive and negative) and the hardware housing shall be:
at least 20 M at a relative humidity of 45-80% and ambient temperatures
from
+15 to +35C.
at least 1 M at a relative humidity of 953% and an ambient temperature of
205C. Insulation resistance shall be measured at a voltage of ±10VDC.
•
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4.1.3. Insulation Dielectric Strength
Insulation resistance between the primary power circuits (both positive and
negative) and the hardware housing, as well as between any electrically isolated
circuits, must satisfy the requirement for electrical resistance of insulation
following the application of test voltage of ±100VDC to those circuits.
The test voltage must not exceed allowable values for test voltages for the
components used in the hardware.
f [kHz]
F kHz
UQ P[dB V]
100
80
60
40
20
0
0.01
0.1
1
f[MHz]
10
100
5.15.2.
Outside Corners and Edge Rounding Radii
Hardware located along crew translation paths, as well as any hardware requiring an
interface during EVA operations must have rounded corners and faces or protection devices for
the corners as specified in Table 30.
Outside hardware, which will be brought into the pressurized volume for scheduled
maintenance or storage, must comply with the requirements defined in paragraph 5.15.3.
Table 30. Rounding Radii for Edges and Corners
Remarks:
Application
Openings, panels, covers (radii
of corners in panel plane)
Exposed corners
Exposed faces:
(1)
2.0 mm
thickness or greater
(2)
0.5 – 2.0 mm
thickness
(3)
less than 0.5
mm thickness
Working with small-size
hardware with a spacesuit
gloved hand.
Small rounding of less than 4.8
mm
Radius
Outside
6.4
3.0
13.0
Remark
Inside
3.0
1.5
Preferred
Minimum
Minimum
Minimum
≥1.0
full radius;
smooth or
rounded
1.0
1.0
Minimum
required to
prevent damage
to the glove.
Absolute
minimum except
for corner
rounding angles
more than 120
degrees