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ANNEXURE-II-Reliability and Quality Assurance Requirements
CRYSTAL BAND PASS FILTERS
CPUR 2018005747
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1 CONTENTS
RELIABILITY AND QUALITY ASSURANCE (R & QA) ....................................................................... 4
1 RELIABILITY ..................................................................................................................................... 4
1.1 LIFE ............................................................................................................................................. 4
1.2 RELIABILITY ANALYSIS ........................................................................................................ 4
2 ENVIRONMENTAL CONDITIONS .................................................................................................. 4
2.1 NON-OPERATING ENVIRONMENT ....................................................................................... 4
2.2 OPERATING ENVIRONMENT ................................................................................................. 4
2.3 VIBRATION ................................................................................................................................ 5
2.4 EMI / EMC SHIELDING ............................................................................................................. 5
3 PARTS AND MATERIALS ................................................................................................................ 5
3.1 PARTS ......................................................................................................................................... 5
3.1.1 DESIGN VERIFICATION MODEL PARTS ...................................................................... 5
3.1.2 FLIGHT MODEL PARTS ................................................................................................... 5
3.2 MATERIALS ............................................................................................................................... 6
4 PROCESSES ........................................................................................................................................ 6
5 MARKING AND IDENTIFICATION ................................................................................................ 7
6 TRANSPORTATION .......................................................................................................................... 8
7 SPACE HERITAGE AND DESIGN QUALIFICATION REQUIREMENTS.................................... 8
8 TEST PROGRAMME .......................................................................................................................... 9
8.1 PHASE-1: DESIGN VERIFICATION PROGRAMME .............................................................. 9
8.2 PHASE-2: SCREENING AND LOT ACCEPTANCE TEST (LAT) PROGRAMME ............... 9
8.3 LOT FORMATION ..................................................................................................................... 9
8.4 FINAL PRODUCTION TEST ..................................................................................................... 9
8.5 SCREENING TEST ..................................................................................................................... 9
8.6 LOT ACCEPTANCE TEST (LAT) ........................................................................................... 10
8.7 FAILURE CRITERIA ................................................................................................................ 10
9 TEST PLAN ....................................................................................................................................... 12
9.1 PHASE-1: DESIGN VERIFICATION MODEL ...................................................................... 12
9.2 PHASE-2: FLIGHT MODEL ................................................................................................... 12
9.3 PARAMETERS TO BE MEASURED AFTER ENVIRONMENTAL TESTS ........................ 12
9.4 TOLERANCES .......................................................................................................................... 12
9.4.1 TOLERANCE OVER OPERATING TEMPERATURE RANGE .................................... 12
9.4.2 TOLERANCE ON TEST CONDITIONS .......................................................................... 13
TABLE – 1: SCREENING AND LOT ACCEPTANCE TEST......................................................... 13
10 TESTS & TEST CONDITIONS .................................................................................................... 14
10.1 VISUAL INSPECTION ............................................................................................................. 14
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10.2 PHYSICAL MEASUREMENT ................................................................................................. 14
10.3 INITIAL PERFORMANCE TEST ............................................................................................ 14
10.4 STABILISATION BAKE .......................................................................................................... 14
10.5 THERMAL SHOCK .................................................................................................................. 14
10.6 TEMPERATURE STORAGE ................................................................................................... 15
10.7 TEMPERATURE OPERATIONAL TEST ............................................................................... 15
10.8 VIBRATION .............................................................................................................................. 16
10.8.1 SINE VIBRATION ............................................................................................................ 16
10.8.2 RANDOM VIBRATION ................................................................................................... 16
10.9 LEAK TEST ............................................................................................................................... 16
10.9.1 FINE LEAK ....................................................................................................................... 16
10.9.2 GROSS LEAK ................................................................................................................... 16
10.10 THERMOVACUUM TEST ................................................................................................... 16
10.11 HUMIDITY TEST ................................................................................................................. 17
10.12 FINAL PERFORMANCE TEST ........................................................................................... 17
10.13 SOLDERABILITY ................................................................................................................ 17
10.14 TERMINAL STRENGTH...................................................................................................... 18
11 LIST OF DOCUMENTS TO ACCOMPANY THE QUOTE ........................................................ 18
11.1 LIST OF DOCUMENTS ALONG WITH THE TECHNICAL QUOTE .................................. 18
11.2 LIST OF DOCUMENTS REQUIRED AFTER AWARD OF CONTRACT ............................ 18
11.3 TEST DATA REPORTS ALONG WITH DELIVERABLES ................................................... 19
12 GENERAL ..................................................................................................................................... 19
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RELIABILITY AND QUALITY ASSURANCE (R & QA)
Reliability and quality are important prerequisites of any space programme hardware. It is
therefore very essential for the vendor to understand and implement the R & QA requirements
judiciously. This section provides the details on R & QA requirements that shall be assured for
this programme.
1 RELIABILITY
1.1 LIFE
a) The unit shall meet all the design requirements for use onboard spacecraft with a minimum
life for 18 years.
b) The unit shall be capable of meeting all the functional requirements at various Spacecraft
assembly and storage as follows;
- 5 years in controlled environmental conditions. The vendor shall specify the exact
method of storage and retest criteria in case of longer storage.
- 3 years storage and life at various levels of spacecraft assembly.
1.2 RELIABILITY ANALYSIS
Manufacturer shall provide complete reliability analysis in terms of reliability estimation with
stress (derating) analysis, FMECA and worst-case drift and tolerance analysis. The Crystal filter
shall be designed and fabricated to achieve a failure rate of better than 0.08 x 10-06 per Hour at
the end of 15 years in orbit.
The reliability calculation shall be carried out as per MIL-HDBK-217F. The vendor should also
specify in analysis report, the methodology used in arriving the failure rate of Crystal Filters and
other components not mentioned in MIL-HDBK-217F. Vendor may propose any alternate
method for reliability analysis per standards for space parts.
2 ENVIRONMENTAL CONDITIONS
2.1 NON-OPERATING ENVIRONMENT
The units shall be capable of withstanding following environmental conditions.
a) TEMPERATURE RANGE : -50°C to +85°C
b) PRESSURE : Ambient to 10-10 torr
c) RELATIVE HUMIDITY : Up to 95% without condensation of
water at +40°C
2.2 OPERATING ENVIRONMENT
a) TEMPERATURE RANGE
Flight Model : -10°C to +60°C
Lot Acceptance Test : -15°C to +65°C
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b) PRESSURE : Ambient, 10-10 torr
c) Relative Humidity : Up to 95% without condensation of water at 40°C
(Applicable for lab test only)
2.3 VIBRATION
The unit shall be designed and fabricated to meet the vibration (Sine and Random) requirements
as specified in this annexure.
2.4 EMI / EMC SHIELDING
The unit shall be designed for both magnetic and EMI shielding as per the requirements of MIL-
STD-461E.
3 PARTS AND MATERIALS
Parts and materials to be used in Units shall be selected from qualified parts and materials list
and through a qualified sub-vendor normally associated with long life satellite hardware.
Necessary certification showing compliance with this requirement shall be supplied along with
the units.
3.1 PARTS
3.1.1 DESIGN VERIFICATION MODEL PARTS
The quality of parts proposed to be used shall be as follows:
a) Passive Parts : ESCC level C3 or with failure level "M" or better
b) Crystals : ESCC level C3 or as per MIL-C-3098
3.1.2 FLIGHT MODEL PARTS
For flight model, the component quality level shall be as follows:
a) Passive Parts : ESCC level B3 or with failure rate level "S" or better
b) Crystals : The following order of preference shall be followed.
First preference: Qualified to ESCC level B3 or MIL-C-3098 with group B testing
Second preference: Non-qualified crystal from QPL/QML vendor. In this case
crystal shall be subjected to Screening, Group A, B and C testing for S Level, as per
the requirements of MIL-PRF-3098.
In the case of passive electronic parts quality levels being lower than the requirements of Para
3.1.2, Parts only from MIL/ESA QPL/QML manufacturer or ISRO qualified manufacturer shall
be used. Such parts shall have sufficient space flight history and DPA and Verification of
Quality (VOQ) shall be performed along with appropriate up-screening. Vendors, in such cases,
shall submit the proposed parts usage list to ISRO for review.
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The electronic parts used should not be of date code older than TWO years, at the time of
FILTER manufacturing. In the case, that devices with recent codes are not available, a
rescreening plan for these devices is to be submitted for review by ISRO and only after
completion of such rescreening tests, these devices may be used. Parts older than 5 years shall
not be used.
3.2 MATERIALS
Ferrous and non-ferrous materials used shall be corrosion resistance type or suitably treated to
resist corrosion, oxidation, tarnishing caused by atmospheric conditions existent in storage or
normal operational conditions. Non-magnetic materials shall be used for all parts except where
magnetic materials are essential. A uniform plating thickness, preferably nickel, shall be applied
all over the crystal BPF body. Plating thickness shall be minimum 1mil.
It is to be noted that Brass and Cadmium plated components and surfaces shall not be used at
any stage of FILTER fabrication. If any such material is proposed by Vendor(s), they shall
submit the proposed material list to ISRO for review and approval.
Materials that are nutrient for fungus shall not be used. Organic and inorganic materials shall be
stable under atmospheric and high vacuum conditions. These materials shall have Total Mass
Loss (TML) less than 1% and Collected Volatile Condensable Material (CVCM) of less than
0.1% when subjected to 125°C and 10-6 torr pressure for 24 hours as per ASTM-E-595. Only
space-qualified epoxies, potting materials, etc. shall be used within their shelf life and cure
schedule specified by the manufacturer. However, their use shall be restricted and failures due to
these shall be recorded and analysed as and when they are detected.
The selection and use of dissimilar materials shall be avoided, where it is impractical to avoid
dissimilar materials in direct contact with each other, suitable protection shall be provided by
space proven coating-plating etc.
4 PROCESSES
The unit shall be built to the standards normally associated with long life satellite hardware. All
the fabrication processes including surface treatment (like plating, painting etc) should be the
qualified processes for space applications. Vendors shall submit their most recent process
qualification status along with the proposal. No, non-qualified process shall be used for crystal
filter fabrication. Particular attention shall be paid, as a minimum, in respect to the following:
Neat clean, smooth and fully wetted homogeneous solder joints
Eliminate bubble entrapment in coatings / epoxies where ever used
All components including torroidal / bead inductors / coils shall be suitably supported on
PCB by suitable potting compound
Wherever wires are attached to casing for grounding etc., a higher melting point solder than
that used for lid soldering, shall be used
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The input / output connections on pins from the PCB etc. shall also be made with high
melting point solder to avoid detachment of these connections while soldering the pins to
external system using SN 63 solder
The marking and plating etc. shall be permanent and should not get damaged during normal
cleaning process using isopropyl Alcohol and other cleaning solvents approved for the
fabrication of electronic hardware. Further, a list of recommended solvents may be provided
to ISRO.
All tolerances not specified shall be consistent with the best engineering practices. Units shall be
uniform in quality and free from blemishes and defects.
5 MARKING AND IDENTIFICATION
The unit shall be identified by assigning unique serial number on the exterior surface by a
suitable process applicable for space use. Marking shall not degrade the performance of the unit.
In addition to functional marking like input/output, etc. following marking shall appear on each
unit:
a) Center Frequency
b) Part name : XTL Filter
c) Part Number
d) Specification Number/Contract Number
e) Serial Number
f) Name of the Manufacturer
g) Date Code (in YYWW format, where YY represents last two digits of
year and WW represents week number of manufacture of unit)
Suggested part no. : XTL aaa.aaaa MHz 02 SMT ccc.ccc kHz RFP
Where,
aaa.aaaa : CF of filter
bb : Type as defined in electrical spec.
ccc.ccc : 3 dB bandwidth in KHz
The permanency of the marking shall be sufficient to withstand the specified environmental
conditions and normal cleaning operations using isopropyl alcohol and other cleaning solvents.
The test method to demonstrate the same shall be specified by the vendor.
In case of space constraints for marking on units, the information may be put on primary
box/data documentation with cross references to build records.
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6 TRANSPORTATION
Each unit shall be packaged in individual ESD protective package. This package shall protect the
unit from environmental conditions during transportation like heat, humidity dust. Each
individual container shall have a moisture absorbing material inside. This individual container
shall then be placed in a transportation container more than one individual unit packages may be
placed in transportation container. Transportation container shall protect the units from heat,
humidity, dust, mechanical shock & vibrations during transportation. The transportation
container shall conform to the applicable carrier rules and regulations and may be the
contractor's commercial practice. The shipping package shall contain all the necessary technical
documents as specified and the necessary commercial documents.
In addition to other mandatory shipping markings, the following additional marking shall appear
on the shipping packages in bold letters:
"HANDLE WITH CARE / HIGH-RELIABILITY COMPONENTS"
"To be opened under clean environment with ESD protection only"
"Store in a cool and dry place"
7 SPACE HERITAGE AND DESIGN QUALIFICATION
REQUIREMENTS
Vendor shall provide details of one (or more, if any) FILTER which is most similar to the
proposed design and is qualified for space use. Vendors should supply qualification report
summary which should necessarily include (apart from other details):
1. Electrical specifications including Centre frequency, BW & Rejection
2. Operating & non-operating temperature range
3. Vibration and shock test conditions etc.
4. Life Test details including test duration and temperature conditions
5. Product specific space flight history of the offered design
6. Name of program
It is to be noted that information required as in points (1) to (6) above is MANDATORY.
Vendor to clearly state all the details so that similarity of the proposed design with that of
qualified design could be assessed.
After review of the space flight heritage and the qualification report, ISRO shall decide
suitability of the proposed part for required application as well as requirement of the DVM
phase. Design verification phase may be required if proposed design has no space flight
heritage. Designs not qualified for space shall not be considered.
Quotes from vendors with no space heritage and/or no design qualified to space requirements
will not be considered.
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8 TEST PROGRAMME
The total program has been divided in two phases:
a) DESIGN VERIFICATION PROGRAMME
b) SCREENING AND LOT ACCEPTANCE TEST (LAT) PROGRAMME
8.1 PHASE-1: DESIGN VERIFICATION PROGRAMME
DVM units and shall undergo the testing as specified in this annexure. These units should meet
all electrical and mechanical specifications and should be identical to the flight hardware in all
respect except for the quality of the parts used (refer Para 3.1: Parts). Go ahead, for Phase-2 shall
be given only after successful completion of Phase-1 (DVM programme), if applicable.
8.2 PHASE-2: SCREENING AND LOT ACCEPTANCE TEST (LAT)
PROGRAMME
All the units shall undergo Screening and Lot Acceptance Test Programme as given in flow
chart (Figure-1.0) before they are acceptable to ISRO.
8.3 LOT FORMATION
The term Lot is defined to be consisting of each type of units manufactured from the same batch
of raw materials at the same time on the same production and assembly line, having all the
provisions for quality assurance. The unit shall satisfy all design, performance and
environmental requirements of the specifications.
8.4 FINAL PRODUCTION TEST
The Final Production Tests are part of tests carried out by the vendor before the units are finally
ready for screening tests. This shall include following as a minimum:
Pre cap visual inspection and Physical dimension measurements
Crystal Aging
The vendor shall specify and provide the details of Final Production Tests and assembly
sequence along with the response to this RFP.
8.5 SCREENING TEST
All the units in the lot formed shall undergo 100% Screening Test as per Table-1. Units not
meeting the specified limits shall be removed from the lot. Maximum of 5% failures are allowed
during screening.
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8.6 LOT ACCEPTANCE TEST (LAT)
On successful completion of Screening Test as per Table 1, Lot Acceptance Test (LAT) shall be
carried out on 5% samples of the lot or minimum one unit randomly selected from screened lot,
as per Table-1. Depending on the center frequency specification, selection of filter types to be
subjected to LAT shall be decided. During Lot Acceptance Test, no failure shall be allowed.
8.7 FAILURE CRITERIA
The units fall-out during Screening Test shall be prepared and submitted to ISRO. This shall
state the number of times that each test parameter failed and quantity of units failed one or more
test parameter. This shall identify all catastrophic failures and failure modes observed.
For number of failures more than 5% of lot during screening, or any failure during LAT, the
entire lot will be rejected. However, vendor may carry out the failure analysis thoroughly and
submit the failure analysis report to ISRO. After review of the failure analysis report, ISRO may
consider accepting the lot with re-work and retest.
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FIGURE-1.0: FLOW CHART FOR SCREENING / LAT PROGRAMME
No
No Yes
Yes
No
LOT ACCEPTANCE TEST AS PER TABLE-
1 ON 5 % (TBD) OF RANDOMLY
SELECTED SAMPLE
Failures observed?
SCREENING TESTS AS PER
TABLE-1
No. of failures
< 5% of lot?
DELIVERABLES
FABRICATION OF FM
UNITS
IN
A SINGLE LOT
DVM (if applicable)
Accepted by ISRO?
FABRICATION OF DVM
UNIT
Yes
Yes
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9 TEST PLAN
9.1 PHASE-1: DESIGN VERIFICATION MODEL
Following tests, with details as per Para 10 in this annexure, shall be conducted on Design
Verification Model:
1) External Visual Inspection
2) Physical Measurement
3) Initial Performance
4) Temperature Operational test
5) Final Performance test
Vendor shall supply test fixture for the electrical testing of the filters along with the deliverables
(DVM).
9.2 PHASE-2: FLIGHT MODEL
The manufacturer shall submit the test plan for the functional and environmental tests to be
conducted on the units during the screening and Lot Acceptance Test programme. The test plan
shall include but not limited to the tests and specification in the sequence as indicated in Table1.
The test plan shall also include the procedure for conducting each test, the test equipment used
and their calibration, total uncertainty for each test set-up and parameter tolerance / limits for the
unit under test. Suitable buffer connections shall be provided during testing.
Vendor shall supply test fixture for the electrical testing of the filters along with the FM
deliverables, if Phase-1 (DVM) is not applicable.
9.3 PARAMETERS TO BE MEASURED AFTER ENVIRONMENTAL
TESTS
All electrical parameters as per electrical specifications.
9.4 TOLERANCES
9.4.1 TOLERANCE OVER OPERATING TEMPERATURE RANGE
Tolerance over operating temperature range shall be as defined in Electrical
Specifications for:
1) Insertion loss 2) Bandwidth 3) Rejection / Attenuation
Note: The above are related to the initial value at ambient. Absolute values shall comply with
the specifications.
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9.4.2 TOLERANCE ON TEST CONDITIONS
Maximum allowed tolerances on test conditions are as given below:
Temperature : ± 3°C
Atmospheric Pressure
Greater than 0.1 torr : ± 5%
Less than 0.1 torr : ± 50%
Relative Humidity : + 0%, -5%
Acceleration : ± 10%
Vibration Frequency : ± 2% above 25 Hz, 0.5 Hz below 25 Hz
Sinusoidal Amplitude : ± 10%
Random (g-rms) : ± 10%
PSD 20-300 Hz : ± 1.5 dB
300-2000 Hz : ± 3.0 dB
TABLE – 1: DVM, SCREENING AND LOT ACCEPTANCE TEST
Sr. No. TEST DVM
SCREENING LOT
ACCEPTANCE
1. VISUAL INSPECTION √ √ √
2. PHYSICAL
MEASUREMENTS
√ √ √
3. INITIAL PERFORMANCE
TEST
√ √ √
4. STABILISATION BAKE - √ -
5. THERMAL SHOCK - √ √
6. TEMPERATURE STORAGE - √ √
7. TEMPERATURE
OPERATIONAL
√ √ √
8.
VIBRATION
- Sine
- Random
-
-
√
√
√
9. LEAK TEST - √ √
10. THERMAL VACUUM - - √
11. HUMIDITY - - √
12. FINAL PERFORMANCE TEST √ √ √
13. SOLDERABILITY - - √
14. TERMINAL STRENGTH - - √
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Note-1: "√" Mark against the test denotes applicability of test. Test details and conditions are
described in Para 10
Note-2: At the end of each environmental test, Electrical Performance checks as per Para 9 and
visual inspection as per Para 10 shall be carried out.
Note-3: The stage, at which solderability and terminal strength test will be performed, shall be
specified by the manufacturer. These tests could be performed either on electrically rejected or
empty packages from the same lot. The manufacturer shall demonstrate that solderability of the
leads does not degrade after completion of Screening and LAT testing.
10 TESTS & TEST CONDITIONS
10.1 VISUAL INSPECTION
Filters shall be visually inspected at 10X magnification minimum. Defects related to
Metallization, surface, finish, discolouration / oxidation, mechanical and workmanship are not
allowed. The defects accept / reject criteria shall be same as those followed for all Hi-Rel
programs. External visual inspection guide lines and accept / reject criteria per
ESA/MIL/NASA-GSFC shall be followed. It is suggested to follow visual inspection
requirements of MIL-STD-883, method 2009. However, the manufacturer shall specify further
details.
10.2 PHYSICAL MEASUREMENT
The mechanical dimension measurements shall be performed as per the agreed fabrication
drawings. Test details to be specified by the manufacturer.
10.3 INITIAL PERFORMANCE TEST
Performance shall be measured for all defined specifications, as per SAC approved test
procedure.
10.4 STABILISATION BAKE
The units shall be stored at maximum non-operating temperature for 48 hours.
10.5 THERMAL SHOCK
Thermal shock test shall be performed as per MIL-STD-202, Method 107, Condition 'A', with
temperature ranges as defined in ENVIRONMENTAL SPECIFICATIONS. The number of
cycles shall be as given below,
Screening : 10 cycles
Lot Acceptance Test : 25 cycles
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At the end of the above sequence a visual inspection shall be conducted to observe any possible
physical degradation of finish/materials or evidence of process deterioration in quality after the
exposure to the high and low temperature conditions.
10.6 TEMPERATURE STORAGE
High and Low temperature storage test shall be performed as per the sequence given below:
Step-1: Stabilize at ambient and perform Functional Test.
Step-2: Store all units at lowest non-operating temperature for 6 hours.
Step-3: At end of 6 hours, stabilize the units at ambient for 1-hour minimum and not more than
24 hours maximum and perform Functional Test as per specifications
Step-4: Store all units at highest non-operating temperature for 6 hours.
Step-5: At end of 6 hours. stabilize the units at Ambient for 1 hour minimum and not more than
24 hours maximum and perform Functional Test as per specifications.
10.7 TEMPERATURE OPERATIONAL TEST
The temperature operational tests shall be performed both during the Screening and LAT testing
for verifying the electrical performances at the specified High and Low operating temperature
limits.
The units shall be placed in a suitable thermal chamber, and connected to the external test set-up
through suitable interconnection. The test shall be conducted according to the following
sequence and conditions:
Step-1: Maintain the chamber temperature at 25 deg C for 1 hour; perform a functional
verification according to the applicable Screening /LAT Test Procedure.
Step-2: Decrease the chamber temperature down to the specified minimum operating limit and
maintain this condition for 1 hour after stabilization
Step-3: While in the above conditions perform a functional verification according to the
applicable Screening /LAT Test Procedure
Step-4: At the end, increase the chamber temperature up to the specified maximum operating
limit and maintain this condition for 1 hour after stabilization
Step-5: While in the above conditions perform a functional verification according to the
applicable Screening /LAT Test Procedure
Step-6: At the end, decrease the chamber temperature to ambient conditions and after 1 hour for
stabilization, perform a functional verification in accordance with the applicable
Screening /LAT Test Procedure.
All the inspection and tests results shall be recorded on the Test Data Record sheets and reported
in the Final Test Report.
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10.8 VIBRATION
10.8.1 SINE VIBRATION
Sine vibration is applicable to LAT only. Sine vibration test shall be carried out as per MIL-
STD-202, Method 204, condition 'E', except the test level and sweep rate shall be as follows.
10 to 2000 Hz : 30 g peak
Sweep Rate : 2 Octave/Min.
No. of sweeps : FOUR (4), per axis (X, Y, Z)
10.8.2 RANDOM VIBRATION
Random vibration test shall be carried out as per MIL-STD-202, Method 214, following
conditions shall apply in all three axis:
Frequency (Hz) Units for Screening Units for LAT
Test level Test level
20-50 + 6 dB/Octave + 6 dB/Octave
50-1200 0.20 g2/Hz 0.45 g2/Hz
1200-2000 - 6 dB/Octave - 6 dB/Octave
Overall Level 18.2 g rms 27.2 g rms
Duration 1 minute/axis 4 minute/axis
10.9 LEAK TEST
The Leak test shall be carried out on all hermetically sealed units only.
10.9.1 FINE LEAK
The test shall be carried out as per MIL-STD-202, METHOD 112, condition C The maximum
leak rate shall not exceed 5 X 10-7 atm cc/sec.
10.9.2 GROSS LEAK
The gross leak test shall be carried out as per MIL-STD-202, METHOD 112, condition B or D.
10.10 THERMOVACUUM TEST
Thermal vacuum test is applicable to all units subjected to LAT testing and shall be conducted
under vacuum condition of 10-06 torr or better. The temperature limits shall be as specified in
Para 2. Thermo-vacuum test profile shall include FIVE cycles as per Fig.2. First cycle shall be
performed at non-operating temperature limits and no RF signal shall be applied during this
cycle. Remaining four cycles shall be performed at the operating temperature limits and the unit
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shall continuously be ON (with nominal Power) during FOUR (4) cycles. The dwell time at
each temperature extreme shall be TWO (2) Hours minimum. The performance measurements,
with points marked as ‘cross-marks’ in Fig 2, shall be carried out during High and Low
temperature soak (dwell time). The duration of the soak may be extended for completion of
performance measurement tests.
FIG 2: THERMO VACUUM TEST PROFILE
10.11 HUMIDITY TEST
The test shall be carried out as per MIL-STD-202, Method 103, Condition 'A' for non-
hermetically sealed units. For hermetically sealed unit, the moisture resistance test as per MIL-
STD-202, Method 106 shall be carried out.
10.12 FINAL PERFORMANCE TEST
Performance shall be measured for all defined specifications, as per SAC approved test
procedure. Also, this shall confirm no degradations are observed after environmental tests.
10.13 SOLDERABILITY
Solderability test shall be carried out as per MIL-STD-202, method 208.
25
-50
85
-15
65
-15
65
-15
65
-15
65
-15
25
-60
-50
-40
-30
-20
-10
0
10
20
30
40
50
60
70
80
90
FIG 2: THERMOVACUUM TEST PROFILE
TEMP (DEG C) MEASUREMENT POINT
2 Hrs
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10.14 TERMINAL STRENGTH
Terminal strength test shall be carried as per MIL-STD-202, Method 211. The manufacturer
shall specify the test conditions. This test may be carried out on electrically reject unit/identical
dummy unit.
11 LIST OF DOCUMENTS TO ACCOMPANY THE QUOTE
11.1 LIST OF DOCUMENTS ALONG WITH THE TECHNICAL QUOTE
The following documents shall accompany the quotes. These are necessary in order to evaluate
the offer. Without these details, the quote from the vendor is liable to be rejected.
1) Point by Point Compliance to Electrical & mechanical specifications and each section of
R & QA Requirements with specific details and offered specifications
2) Space History/Space Program to which similar design items have been supplied.
3) Qualification report summary for similar design units listing device specifications, Test
plan, test conditions and results.
4) Detailed technical data sheet indicating electrical, mechanical (including Specification
control drawing (SCD)/Interface control drawing), package outline details with
dimensions, environmental specifications and ordering information.
5) Quotes from manufacturer having space heritage of product with similar design will only
be considered.
6) All the technical information to be supplied additionally as soft copy on CD/DVD (along
with the hard copies). It is to be noted that cost information should not be included in
this soft copy.
7) List of all parts and materials proposed to be used for this programme. Quality levels,
Qualification status of the parts and outgassing details of the materials proposed to be
used for flight model units.
8) Typical Failure rate value
9) Screening/Qualification Plans (if other than proposed R & QA requirement in this
document)
10) Quality Control Plan
11) Non-conformance Control Plan
12) Configuration change control Plan
11.2 LIST OF DOCUMENTS REQUIRED AFTER AWARD OF
CONTRACT
Apart from the documents required along with technical offer, vendor shall supply the reports as
mentioned below, but not limited to, at appropriate stages after the award of contract. This list is
tentative and will be finalised during purchase order placement. These have to be full reports
(not the summary reports):
-
Annexure-II_4_(R&QA)-Hi Rel Crystal BPF-CPUR 2018 00 5747.docx Page 19 of 19
1) List of parts, materials, their quality levels, derating criteria followed, traceability data,
purchase history etc.
2) Documents containing test procedures, test and calibration facilities, environmental
facilities and relevant operation details
3) Reliability Analysis Report
4) Non-conformance (parts and materials) test reports
5) [FOR FAILURES REPORTED, IF ANY] Failure reports (for catastrophic failures),
mechanical or handling failures, malfunctioning or operative deviations from the
specifications along with corrective actions
6) Thermal design analysis report
7) Mechanical design analysis report
11.3 TEST DATA REPORTS ALONG WITH DELIVERABLES
1) Certificate of compliance (CoC)
2) Test data reports of Screening & LAT, as soft copies
12 GENERAL
1) The deliverables shall consist of:
(i) Certificate of Conformance
(ii) DVM Units (if applicable)
(iii) FM units
(iv) LAT units
(v) Test data package of FM and LAT units
(vi) Two sets of Test fixture for electrical testing of filters (at DVM /FM stage, as
applicable)
2) The cost of each test is to be indicated separately in the proposal. Based on the quality,
previous qualification and space flight history details from the supplier in the proposal,
SAC may remove any test or group of tests in the final order. Vendor shall quote for test
fixtures as a separate item.
3) All the data/drawings should be provided on a Microsoft Windows compatible CD/DVD
along with a hardcopy. The drawings / ICD, preferably, should be in AUTOCAD and
test data in Microsoft Office.
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