REQUEST FOR PROPOSAL OF · REQUEST FOR PROPOSAL (RFP) – KU-BAND HIGH POWER WAVEGUIDE CIRCULATORS...
Transcript of REQUEST FOR PROPOSAL OF · REQUEST FOR PROPOSAL (RFP) – KU-BAND HIGH POWER WAVEGUIDE CIRCULATORS...
KU BAND WAVEGUIDE CIRCULATORS and TERMINATIONS
REQUEST FOR PROPOSAL
OF
KU BAND WAVEGUIDE CIRCULATORS and TERMINATIONS
(SAC-GCP-XI -RFP-12-09)
(JULY 2012)
GOVERNMENT OF INDIA
SPACE APPLICATIONS CENTRE
INDIAN SPACE RESEARCH ORGANISATION
AHMEDABAD – 380 015
INDIA
CONTENTS
INTRODUCTION
EXHIBIT-A
BACKGROUND
EXHIBIT-B
1.0 INTRODUCTION
2.0 GUIDELINES FOR PREPARING TECHNICAL DETAILS
3.0 GUIDELINES FOR PREPARING QUOTATIONS
EXHIBIT-C
1.0 RELIABILITY
1.1. LIFE
1.2 RELIABILITY
2.0 ENVIRONMENTAL CONDITIONS
2.1 NON-OPERATING ENVIRONMENT
2.2 OPERATING ENVIRONMENT
2.3 VIBRATION/SHOCK
2.4 EMI/EMC SHIELDING
3.0 PARTS AND MATERIALS
4.0 PROCESSES
5.0 MARKING AND IDENTIFICATION
6.0 TRANSPORTATION
7.0 SCREENING AND LOT ACCEPTANCE TEST (LAT)
7.1 SCREENING
7.2 LOT ACCEPTANCE TESTING
7.3 FAILURE CRITERIA
8.0 TOLERANCES
8.1 PARAMETERS TO BE MEASURED AFTER ENVIRONMENTAL TEST
8.2 PARAMETER TOLERANCE OVER OP. TEMP.
8.3 TOLERANCE ON TEST CONDITIONS
9.0 TEST DETAILS
9.1 VISUAL INSPECTION
9.2 PHYSICAL MEASUREMENT
9.3 INITIAL PERFORMANCE TEST
9.4 EMI/EMC TEST
9.5 THERMAL SHOCK
9.6 TEMPERATURE STORAGE
9.7 TEMPERATURE OPERATIONAL TEST
9.8 VIBRATION
9.8.1 SINE VIBRATION
9.8.2 RANDOM
9.9 THERMAL VACUUM TEST
9.10 POWER HANDLING TEST
9.11 MULTIPACTOR TEST
9.12 FINAL PERFORMANCE TEST
9.13 RESISTANCE TO SOLVENTS
10.0 LIST OF DOCUMENTS
11.0 GENERAL
EXHIBIT-D
TECHNICAL SPECIFICATIONS
EXHIBIT-E
QUANTITIES & SCHEDULES
1.0 QUANTITY
2.0 DELIVERY SCHEDULE
3.0 WARRANTY
REQUEST FOR PROPOSAL (RFP) – KU-BAND HIGH POWER WAVEGUIDE
CIRCULATORS AND TERMINATIONSS
INTRODUCTION
The Indian Space Research Organisation (ISRO) requests your company to submit
quotation for space qualified KU-BAND HIGH POWER WAVEGUIDE CIRCULATORS
AND TERMINATIONSS, as detailed in this document. These will be used in the Flight
Models of the Communication /Broadcast Satellite Service Pay TERMINATIONSs of
INSAT & GSAT series Operational Spacecrafts. This document consists of five sections:
EXHIBIT-A: Gives the general background of the Project for which the units are required.
EXHIBIT-B: Gives the details which vendor shall follow for preparing the response
against this RFP.
EXHIBIT-C: Gives the Reliability and Quality Assurance requirements.
EXHIBIT-D: Gives the Electrical Specifications.
EXHIBIT-E: Gives the details on quantity, delivery schedules and warranty.
EXHIBIT-A
BACKGROUND
1.0 The Indian National Satellite System (INSAT) is a domestic multipurpose system,
using satellites in geo-stationary orbit, for long distance telecommunications, Radio
and TV programme distribution, meteorological earth-observation, data relay,
search and rescue. The Department of Space of the Government of India, which has
the responsibility for establishing and maintaining the INSAT space segment, has
embarked on development and fabrication of INSAT and GSAT series Spacecrafts.
2.0 The GSAT satellite series is designed to be compatible with most of the commercially
available launchers and also the Indian Geosynchronous Launch Vehicle (GSLV),
which is under development. The items under procurement are to be used for the
development / fabrication of GSAT satellites.
3.0 For fabrication of these GSAT Spacecrafts, the Department of Space of the
Government of India, through its Indian Space Research Organisation (ISRO), is
planning to purchase certain spacecraft components and related services. Since
your company is a supplier of components for our / other satellite projects, we are
requesting, proposals from you for similar products and services for the GSAT
project.
4.0 It is very important for our evaluation of offer that your proposal also includes
sufficient technical data on form, fit and function. If this technical data is not in public
domain, we request that you apply in advance to your Department of State for a
license to export this technical data in your proposals.
EXHIBIT - B
GUIDELINES TO VENDORS
1.0 INTRODUCTION
The total program has been divided in two phases:
PHASE-1 - DESIGN VERIFICATION MODEL:
Requirement of DVM unit shall be decided based on qualification status and space
heritage. Vendor shall provide details regarding Space flight Heritage, overall as well as
specific to the quoted part, Qualification status, Qualification report summary along with
the quote. If DVM unit is required, then one Circulator & TERMINATIONS shall be
supplied as per the agreed delivery schedule.
These units are required for design verification only and need not under go the complete
testing. These should meet all electrical and mechanical specifications and should be
identical to the flight hardware in all respect.
PHASE-2 - FLIGHT MODEL:
Delivery of flight hardware fully tested as per Exhibit-C requirements and Lot Acceptance
tests carried out (as per Figure-1) on samples.
Go-ahead for phase-2 will be given subject to successful completion of phase-1
(Wherever applicable).
2.0 GUIDELINES FOR PREPARING TECHNICAL DETAILS
2.1 These are very special hardware and ONLY THOSE VENDORS who have
adequate experience in
a) Design, development and fabrication of Hi-Rel systems
b) Qualification of such hardware for onboard communication, satellites should
respond and quote against this RFP.
2.2 The vendor is requested to examine the RFP thoroughly and offer
compliance/non-compliance point by point. In case of non-compliance, the
deviation from the specified parameter shall be furnished and for complied
parameters the vendor specification (better or same) shall be provided.
2.3 The vendor should also submit compliance statement consisting of compliance /
non compliance with test philosophy, test plans and other requirements as detailed
in Exhibit-C under "Reliability & Quality Assurance Requirements". The vendor
may submit the Screening /Lot Acceptance testing programme which might have
been used for supplying similar hardware for other space missions. If compliance
statement is not supplied along with the quote, the offer will not be considered.
2.4 It is necessary for the vendor to furnish complete information as required in various
exhibits (-B to -E) of this RFP for proper evaluation and assessment of his proposal.
2.5 The vendor can attach additional information, if any, which may provide more
information on these products.
2.7 The vendor may seek clarifications, if any, in advance before submitting the
quotations. However, any clarification thus sent to the vendor will also be sent to all
other vendors.
2.8 The vendor shall give complete qualification status, flight history, space programme
details and failure data etc. along with the response.
3.0 GUIDELINES FOR PREPARING QUOTATIONS
3.1 The quotation shall include, in addition to unit cost, all the prices towards screening,
qualification, acceptance and lot-acceptance testing etc. The cost break up should
include charges for each test to enable SAC in deciding to include/exclude any test
depending on the cost and schedule constraints. The break up of overall cost in
terms of Phase-1 and 2 (as defined in para 1.0) also needs to be indicated.
3.2 This requirement is for flight hardware but the order may also include one (1) unit of
design verification units which are required to confirm the electrical, mechanical
specifications, quality assurance etc. The each type of flight hardware shall be
subjected to proto / qualification testing on the representative basis.
3.4 The vendor is requested to acknowledge the receipt of this RFP and his
willingness/inability to respond and quote against this RFP.
3.5 The vendor must ensure that his quotation along with all the details reaches
SAC/ISRO before the due date.
3.6 The quotation shall consist of two parts:
a) PART-1 : `Detailed Technical Proposal'
giving all details as required in Exhibit -C & -D.
b) PART-2 : `Cost & Management Proposal'
giving cost, payment terms and other financial details.
3.7 The supplier shall give preliminary thermal design analysis along with the offer,
particularly for the KU BAND CIRCULATORS and TERMINATIONS. The
detailed analysis shall be provided later.
Note: Part-2 shall be submitted in a separate sealed envelop. This requirement shall be
strictly adhered to. However, both parts shall be submitted together in a sealed
envelop.
EXHIBIT-C
RELIABILITY AND QUALITY ASSURANCE (R & QA)
INTRODUCTION
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, which
shall be assured for this programme for Ku band HIGH POWER WAVEGUIDE
CIRCULATOR and TERMINATIONS (referred as „unit‟ in this Exhibit).
1.0 RELIABILITY :
1.1. LIFE :
a) The unit shall meet all the design requirements for use onboard spacecraft with a
minimum life for 15 years.
b) The unit shall be capable of meeting all the functional requirements at various stages
of spacecraft assembly and storage as follows;
- 3 years storage and life at various levels of spacecraft assembly
- 5 years in controlled environmental conditions. The vendor shall specify the
exact method of storage and retest criteria in case of longer storage.
1.2. RELIABILITY ANALYSIS :
The CIRCULATOR / ISOLATOR shall be designed and fabricated to achieve a failure rate
of better than 0.06 x 10-06 per Hour.
2.0 ENVIRONMENTAL CONDITIONS :
2.1. NON-OPERATING ENVIRONMENT :
The units shall be capable of withstanding following environmental conditions:
a) TEMPERATURE RANGE : -55oC to +85oC
b) PRESSURE : Ambient to 10-10 torr
c) RELATIVE HUMIDITY : Upto 95% without condensation of water at +40oC
2.2. OPERATING ENVIRONMENT :
a) Temperature Range :
i) Screening : -20oC to +70oC
ii) Lot Acceptance : -25oC to +75 oC
b) Pressure : Ambient to 10-10 torr
c) Relative Humidity : Up to 95% without condensation of water at 40oC
(Applicable for ground testing only)
The temperatures specified are base plate temperature. Thermal conductance of 1000
W/m2-degC shall be considered. Temperature rise due self heating of unit during operating
conditions with full power under thermo-vacuum conditions at this base plate temperature
shall be specified by vendor and unit shall be designed to operate in these conditions for
15 years on-board communication satellite. There shall not be any non-linearity in unit
performance over the specified operating temperature range wherein the higher
temperature limit shall include temperature rise due to self heating. Vendor shall comply
and demonstrate performance linearity over the temperature.
Unit shall be designed with adequate venting to allow quick depressurization during launch
ascent. Vendor shall demonstrate the same by analysis.
2.3. VIBRATION / SHOCK :
The unit shall be designed and fabricated to meet the vibration (Sine and Random) and
mechanical shock requirements as per the qualification tests mentioned in paragraph 9.0.
2.4. EMI / EMC SHIELDING :
The unit shall be designed for both MAGNETIC and EMI shielding as per MIL-STD-461E.
No RF leakage (Electromagnetic) shall be allowed from the unit. The RF leakage/RF
shielding specification as given in Electrical Specifications shall be complied with.
3.0 PARTS AND MATERIALS :
Parts and materials proposed 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
communication satellite hardware.
The epoxy for coating and adhesion shall not degrade / soften with use of isopropyl
alcohol (electronic grade), normally used for cleaning.
Ferrous and non-ferrous materials used shall be corrosion resistant type or suitably
treated to resist corrosion 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. Materials, which are nutrient for fungus, shall not be
used unless they are in the hermetically sealed containers.
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 test conditions
of 125oC and 10-6 torr pressure for 24 hours. Only space qualified epoxies, potting
materials, etc. shall be used. Their use shall be restricted and failures due to these shall
be recorded as and when they are detected.
The selection and use of dissimilar materials shall be avoided, where it is impractical to
avoid dissimilar metals in direct contact with each other, suitable protection shall be
provided by space proven coating-plating etc.
4.0 PROCESSES :
The unit shall be built to the standards normally associated with long life communication
satellite hardware. Particular attention shall be paid, as a minimum, in respect to the
following :
- Eliminate bubble entrapment in coatings/epoxies wherever used,
- The marking and plating etc. shall be permanent and should not get damaged during
normal cleaning process using Isopropyl Alcohol / Freon and other cleaning solvents
approved for the fabrication of electronic hardware. Further, a list of recommended
solvents may be provided to ISRO.
- Interface dimensions.
- Surface flatness, finish, and plating quality
- Cleanliness and handling of plated / painted surfaces, particularly of the venting holes
All tolerances not specified shall be consistent with the best engineering practices. Units
shall be uniform in quality and free from blemishes and defects.
5.0 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 markings like input/output, frequency etc. following
marking shall appear on each unit:
a) Part name b) Part Number
c) Serial Number d) Port marking (Input / Output marking)
e) Name of the Manufacturer f) Date of Manufacture
h) LAT unit (Applicable to Lot Acceptance Test unit only)
Following part No. shall be applicable for these devices :
P XXXXX-YYYYY-WRZZZ-WWW-NN-RFP
Where , P = C for Circulator, T for TERMINATIONS
XXXXX = Start frequency in MHz (e.g. 10700 for 10.7 GHz)
YYYYY = Stop frequency in MHz (e.g. 11700 for 11.7 GHz)
ZZZ = waveguide interface (e.g. 75 for WR-75) of forward path
WWW = Forward Power handling capability in watts (e.g 150 for 150W)
NN = 1 for TERMINATIONS, 3 for Circulator
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.
6.0 TRANSPORTATION :
Waveguide windows shall be suitably protected to prevent contamination entering the
waveguide cavities, during handling and transportation. The unit shall be packaged in
separate containers to protect against electrical, mechanical and environmental damage.
Each individual container shall have a moisture absorbing material inside. Devices
subjected to Lot Acceptance Test shall be clearly marked as “LAT unit” and “NOT FOR
FM”.
The individual unit package shall be fixed within the shipping package in such a way that
they will be resistant to mechanical shock, humidity and dust. 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"
7.0 SCREENING AND LOT ACCEPTANCE TEST (LAT) :
All the units shall undergo Screening and Lot Acceptance Test (LAT) specified in flow
chart before they are acceptable to ISRO (Figure – 1).
The manufacturer shall submit the test plan for the functional and environmental tests to
be conducted on the units during the Screening (ATP) and LAT (QTP) test programme.
The test plan shall include but not limited to the tests and specification in the sequence
indicated in the Table-1. 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.
7.1. SCREENING :
All the units shall undergo Screening Test as per table-1. Units exceeding the specified
limits shall be removed from the lot.
7.2. LOT ACCEPTANCE TESTING :
On successful completion of Screening Test as per section 7.1, the Lot Acceptance Test
(LAT) shall be carried out on 3% (minimum one) samples, randomly selected from
screened lot of each type as per Table-1. No failure is allowed during LAT.
7.3. FAILURE CRITERIA :
The details of the unit fall-out during Screening Test shall be informed to ISRO. Failure at
any stage shall be reported to ISRO immediately. This shall be followed by detailed failure
analysis. Maximum 5% failures are allowed during screening and No failure is allowed
during LAT. In case of number of failures exceeding this criterion, entire lot shall be
rejected. However, based on failure analysis, ISRO may decide for the acceptance of lot
after necessary corrective actions and retest of units. This shall be decided based on
failure analysis report and implemented by vendor.
8.0 Tolerances :
8.1. Parameters to be measured after environmental test :
- Insertion loss
- Isolation
- Return loss
8.2. Parameter tolerance over operating temperature range with reference to ambient,
(Absolute values shall comply to the specifications) :
- Insertion loss : + 0.05 dB
- Isolation : + 2.0 dB
- Return loss : + 2.0 dB
8.3. Tolerance on Test Conditions :
Maximum allowed tolerances on test conditions are as given below :
Temperature : +1oC
Atmospheric Pressure
Greater than 0.1 torr : + 5%
Less than 0.1 torr : + 50%
Relative Humidity : +0%, -5%
Acceleration : + 10%
Vibration
Frequency : + 2% above 20 Hz, 0.5 Hz below 20 Hz
Sinusoidal Amplitude : + 10%
Random (g-rms) : + 10%
Power Spectral Density
20-300 Hz : + 1.5 dB
300-2000 Hz : + 3.0 dB
Yes
LOT ACCEPTANCE TEST AS PER
TABLE-1 ON 3 % RANDOMLY
SELECTED SAMPLE OF EACH TYPE
Failures
observed?
SCREENING TESTS AS
PER TABLE-1
No. of failures
< 5% of lot?
DELIVERABLES
FABRICATION OF EACH
TYPE OF UNIT IN A
SINGLE LOT
No
Yes No
Yes
FIGURE 1.0: FLOW CHART FOR SCREENING AND LOT ACCEPTANCE
PROGRAMME
TABLE-1 TEST MATRIX for SCREENING and LAT
Sr. No. TEST SCREENING LAT
1. VISUAL INSPECTION X X
2. PHYSICAL MEASUREMENTS X X
3. INITIAL PERFORMANCE TEST X X
4. THERMAL SHOCK X X
5. TEMPERATURE OPERATIONAL X X
6.
VIBRATION
- Sine
- Random
-
X
X
X
7. MECHANICAL / PYRO SHOCK - X
8. EMI / EMC TEST - X
9. THERMO-VACUUM - X
10. POWER HANDLING TEST X X
11. MULTIPACTOR TEST - X
12. FINAL PERFORMANCE TEST X X
13. RESISTANCE TO SOLVENTS - X
Note-1 : At the end or during each environmental test Electrical Performance checks as
per section 8.1 and visual inspection as per Para 9.1 shall be carried out.
Note-2 : "X" Mark against the test denotes applicability of test. Test details and
conditions are described in Para 9.0.
9.0 TEST DETAILS :
9.1. VISUAL INSPECTION :
Visual inspection shall be carried out at 10X (min) magnification. Devices shall be
inspected for material, finish, surface, workmanship related defects. Further details shall
be specified by the vendor giving accept / reject criteria.
9.2. PHYSICAL MEASUREMENT :
Mechanical dimensions of the unit with respect to the ICD shall be measured. ICD shall
specify the surface finish also, and the same shall be verified on sample basis. Test details
to be specified by the manufacturer.
9.3. INITIAL PERFORMANCE TEST :
Full RF characterization shall be carried out as per electrical specification given.
9.4. THERMAL SHOCK :
The test shall be carried out as per MIL-STD-202, Method 107, Condition 'A'. The number
of cycles shall be as given below .Test shall be conducted with cold cycle first.
Screening : 10 cycles
Lot Acceptance : 25 cycles
9.5. 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 -55oC for 6 hours.
Step-3 : At the end of 6 hrs. stabilize the unit at ambient for 1 hour and perform functional
Test.
Step-4 : Store all units at +85oC for 6 hours.
Step-5 : At the end of 6 hours stabilize the unit at ambient for 1 hour and perform
functional Test.
9.6. TEMPERATURE OPERATIONAL TEST :
The temperature operational tests shall be performed both during the Screening and Lot
Acceptance testing programs by verifying the electrical performances at the specified High
and Low operating temperature limits. Vendor shall demonstrate linear performance of the
unit over the specified temperature during the test. Unit with non-linearity shall be rejected.
The units shall be placed in a suitable thermal chamber, and connected with the external
test set-up through an interconnecting plate carrying suitable connectors. The test shall be
conducted according to the following sequence and conditions:
Step-1 : Decrease the chamber temperature down to the specified minimum operating
temperature and maintain this condition for 1 hour after stabilisation;
Step-2 : While in the above conditions perform a functional verification as per Para 8.3
according to the applicable Test Procedure.
Step-3 : At the end, increase the chamber temperature up to the maximum operating
temperature and maintain this condition for 1 hour after stabilization.
Step-4 : While in the above conditions perform a functional verification as per Para 8.3
according to the applicable Test Procedure.
Step-5 : At the end, decrease the chamber temperature at ambient conditions and after
1 hour for stabilization performs a functional verification as per Para 8.3 in
accordance with the applicable Test Procedure.
At the end of the above a visual inspection shall be carried out to verify any possible
physical degradation of materials and processes deterioration after the exposure to the
high and low temperature conditions.
9.7. VIBRATION :
The units shall be subjected to vibration test as specified in following paragraphs. The
natural resonant frequency of the units shall be higher than 100 Hz.
9.7.1. SINE VIBRATION :
Sine Vibration test shall be carried out as per MIL-STD-202, Method 204, condition „E‟,
except the following test levels shall be applicable for all 3 axes :
10 to 2000 Hz, 30 g peak.
Sweep Rate: 2 Octave/Min.
No. of sweeps : 4 per axis
9.7.2 RANDOM :
The test shall be carried out as per MIL-STD-202, Method 214, following conditions shall
apply :
Frequency (Hz) Screening LAT
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 2 minute/axis
9.8. MECHANICAL / PYRO SHOCK TEST :
The units design shall be capable to withstand the mechanical / pyro shock test conditions
given below. Requirement of the compliance demonstration by test shall be decided based
on the Qualification status, Shock test level during qualification and Space flight heritage.
Frequency (Hz) SRS Normal to mounting plane SRS Parallel to mounting plane
100 – 600 15 dB/oct 15 dB/oct
600 – 5000 700 g 400 g
5000 – 10000 - 6 dB/oct - 6 dB/oct
Number of shocks 2 2 per axis
9.9. EMI/ EMC TEST :
The units shall be subjected to RE102 test as per MIL-STD-461E over its operational
frequency band at rated power. Alternatively vendor may perform RF shielding
measurements to demonstrate compliance to electrical specifications of RF shielding. In
case of RF shielding measurements, vendor shall give detailed measurement procedure
with the calculations to derive shielding effectiveness. The radiated emissions shall not
exceed the MIL-STD-461E requirements.
9.10. THERMAL VACUUM TEST :
Thermo-vacuum test shall be carried out only on LAT samples. The test shall be carried
out as per the profile given in fig. 2.0. The test shall consist of five cycles. Dwell time shall
be two (2) hours for all the cycles. The duration of cycle may be extended for completion
of performance measurement tests. Temperature limits shall be storage temperature limit
for first cycle & operating temperature limit (LAT) for remaining four cycles. The insertion
loss and isolation of each unit under test, during transition from each temperature extreme
shall also be monitored and recorded.
9.11. POWER HANDLING TEST :
During screening, Power handling test shall be carried out on 100% units. However,
applicability of power handling test on 100% of lot OR on sample basis shall be decided
based on heritage, qualification status and design capability (design margins). Hence,
vendor shall quote for power handling in quantity slabs. The test shall be conducted under
thermo-vacuum conditions at maximum operating temperature at rated power level. All the
RF paths (where ever applicable) shall be energized at rated power. The test duration
shall be six hours at maximum rated power after temperature stabilization. During the test
body temperature, I/p power, O/p power and reflected power of the unit shall be monitored
and recorded.
9.12. MULTIPACTOR TEST :
Multipactor testing shall be conducted on all the LAT units at the power level specified in
the electrical specifications (Multipactor Threshold – peak power). The test shall be
conducted to demonstrate the multipactor free performance at input power as stated in
“peak power handling capacity ” of electrical specifications, with 25% duty cycle.
9.13. FINAL PERFORMANCE TEST :
This shall be carried out as per electrical specification given in Exhibit-B.
9.14. RESISTANCE TO SOLVENTS
Resistance to solvents shall be carried out as per MIL-STD-202, method 215. The test may
be carried out on electrically rejected samples.
10.0 LIST OF DOCUMENTS
a) The following documents shall accompany the quotes :
Space History / Space Programme to which similar items have been supplied with
frequency of operation and RF power level.
Qualification report summary giving details regarding the list of tests and test
conditions of similar design units.
Mechanical / pyro shock test levels
Qualification power level for the proposed design and multipactor margin
Estimated / measured body temperature of unit at rated power level for the proposed
design (this shall be supplied for all the types).
Generic failure rate
Screening / Qualification Plans
b) Apart from above the documents/reports as given below, but not limited to, shall
be supplied later after the award of contract. These have to be full reports (not the
summary reports) :
List of parts, materials, their quality levels, derating criterion followed, traceability data,
purchase history etc.
Documents containing test procedures (ATP & QTP with test set up details)
Non conformance parts and material test reports
Multipactor analysis
Thermal Analysis at maximum operating temperature and rated power level.
Mechanical / Structural Analysis
Venting Analysis
Non conformance parts and material test reports
Documents containing test procedures, test and calibration facilities, environmental
facilities and relevant operation details.
Failure reports (for catastrophic failures), mechanical or handling failures,
malfunctioning or operative deviations from the specifications along with corrective
actions. In absence of failure report, the entire lot shall be rejected in case of failure.
c) Test data reports of Screening / LAT and certificate of compliance along with the
deliverable units (1 hard copy + 2 soft copies in CD/DVD form) shall be provided.
11.0 GENERAL
11.1 The parts supplied by the manufacturer shall be from a single date code. In case of
the off-the-shelf parts, it should not be older than 2 years from the date of shipment
to SAC.
11.2 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 delete any test or group of tests.
11.3 All the data/drawings should be provided on a CD/DVD with a hardcopy. The
drawings / ICD, preferably, should be in AUTOCAD compatible format and test data
in Microsoft Office.
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EXHIBIT-D
Type-1 WAVEGUIDE CIRCULATOR 12.20– 12.45 GHz
1.0 ELECTRICAL SPECIFICATIONS: Compliance/
Noncompliance
1.1 Operating Frequency Band 12.20 – 12.45 GHz
1.2 Insertion Loss 0.15 dB (max.), 0.1 dB Typical
1.3 Return loss at all ports 23 dB (min)
1.4 Insertion loss slope 0.001 dB/MHz (max)
1.5 Insertion loss change over
any 40 MHz Band
0.02 dB (max)
1.6 Group delay variation over
any 40 MHz Band
0.5 nSec (max)
1.7 Isolation 23.0 dB (min)
1.8 Average Power handling
capacity
150 W minimum in forward
direction
150 W minimum in reverse
direction
(i.e circulator should operate in
fully short circuited
TERMINATIONS condition)
1.9 Radiated Interference < -75 dBi
1.10 Peak Power handling
capacity (multipaction)
600 watts , pulse in forward
direction
1.11 Input/Output ports (W/G) WR-75 ,flange drawing provided
2.0 TEMPERATURE RANGE
Over which electrical
Specifications to be met
-25°C to +75°C (LOT
ACCEPTANCE)
-20°C to +70°C (Screening)
3.0 MECHANICAL SPECIFICATIONS
3.1 Mountings As per given drawing
3.2 Overall Weight 75 gms (approx.)
3.3
Outside Finish of the Flanges
Black Thermal Painted (Except
mating surfaces)
TYPE-2 WAVEGUIDE TERMINATION 10.95 – 12.75 GHz
1.0 ELECTRICAL SPECIFICATIONS: Compliance/
Noncompliance
1.1 Operating Frequency Band
: 10.95 – 12.75 GHz
1.2 Return loss : 23 dB (min)
1.3 Average Power handling Capacity
: 150 W (min)
1.4 Peak Power handling
capacity (multipaction)
600 watts , pulse in
forward direction
1.5 Radiated Interference : < -75 dBi
1.6 Input/Output Ports (w/g) : WR-75 , flange
drawing provided
2.0 TEMPERATURE RANGE:
( Over which electrical
Specifications to be met )
: -25°C to +75°C
(LOT ACCEPTANCE)
: -20°C to +70°C
(Screening)
3.0 MECHANICAL SPECIFICATIONS:
3.1 Mountings : As per given drawing
3.2 Overall Weight : 60 gms. Max
3.3 Outside Finish : Black Thermal
Painted (Except mating
surfaces of the Flanges)
3.4 Inside Finish : Silver plated
3.5 Heat Dissipation : Heat dissipation
through Conduction to
the mounting panel
EXHIBIT-E
QUANTITIES, SCHEDULE AND WARRANTIES
1.0 QUANTITIES
The vendor shall quote in step quantities for KU BAND CIRCULATORS and
TERMINATIONS. As clarified earlier that the requirement is primarily for Flight
hardware however one unit of each may be required to be supplied by the vendor for
design verification (Electrical/Mechanical/Quality etc.) in Phase-1 as per schedules
given below (refer Para 2.0 below).
STEPS OF QUANTITIES
1.1 DESIGN VERIFICATION MODEL
Circulator : 1 No.
Termination : 1 No.
1.2 FLIGHT UNITS
Please quote in quantity slabs of
10-15,16-29,30-50
for KU BAND CIRCULATORS and TERMINATIONS
1.3 LAT Units : Qty. to be decided depending upon the FM quantity
selected. Hence this will be as per para 7.2 of EXIBIT-C.
PLEASE QUOTE IN FOLLOWING FORMAT ONLY
SR NO
ITEM/ TEST CHARGES QTY (SLABS) EACH COST
TOTAL COST
1 DVM 1 XXXXXX XXXXXXXX
2 FM INCLUDING SCREENING (FROM TOTAL FM ORDERED , 5% WILL BE USED AS LAT )
10-15,
16-29,
30-50
XXX XXXXX XXXXXXX
XXXXX XXXXXXX XXXXXXXXX
3 LOT ACCEPTANCE TEST CHARGES ON 5% UNITS /OR AS SUGGESTED BY SAC QA TO ROUNDED UP QUANTITY(EXCLUDING LAT UNITS HARDWARE)
-------- XXXXXXX
4 OTHER CHARGES IF ANY WITH BREAKUP
XXXX XXXXXX
2.0 ORDERING
The order will be placed for total requirement including Deign verification, Lot
Acceptance and Flight models.
3.0 DELIVERY SCHEDULES
Design Verification Model along with
Design Review : WITHIN 2 Months after L/I
Flight Model : WITHIN 6 Months after L/I
LAT Units : WITHIN 8 Months after L/I
4.0 WARRANTY
(a) The vendor shall provide warranty as given below:
“The units supplied here upon shall be free from any defects in material or
workmanship and in accordance with the applicable specifications and drawings”.
(b) This warranty shall run for period of Four years from the date of final acceptance by
SAC/ISRO and shall be in addition to any other rights available to SAC/ISRO. This
warranty shall continue to be valid for corrected or replaced units until four years
after the date of final acceptance by SAC/ISRO of the corrected or replaced parts.