Page 17 - test

Ref : CM-DFH4-2014-1
BEAZLEY Issue : 1

DFH 4 Series Spacecraft Date : 28 Sept 2014
Page 15 of 38

Loasat-1 Observation Comment /Assessment Cri

 Page 102, It will be good to have on block  See comment on the left.
diagram, all redundancies (cold, hot) and the
power distribution.
 Page 106. It seems that the AOCS is similar to  With all the changes in the subsystem, it is
previous design with removing of the IPS. difficult to assess the real heritage.
Avionic  Is the AOCS computer in clod redundancy or is  Difficult to comprehend with the information
Subsystem the second one in standby mode (with all the provided.
context and patches stored in case of a need to
use the redundant). Same question for the
CMU processor.
 Is there an EDAC protection to correct soft  See comment on the left.
errors and prevent SEU effects?
 Page 109-113. If we trust all the good wording  To substantiate the heritage, it will be interesting
on these pages, one can conclude that the solar to get feedback for the in-orbit satellites
array is in good shape. (operational performances versus predictions)
 Coherence between predicted performance
between all the programs to be demonstrated.
 It will be good to know which cell type they  See comment on the left.
Solar Array are using, thickness of the cover glass
minimum distance between cells and max
voltage between adjacent cells. How the inner
panel is populated. What is done to be
protected against ESD charging
 The BABTA / SADM is not described.  See comment on the left.

 Deployment mechanism not described.  Any flight experience?
 Which units need to be modified to  Is there a need to review unit categorization?
accommodate a 100 Volt bus?
 Li-Ion batteries page 122. Some accelerated See comment on the left..
life test are still ongoing. There is a big
EPS difference between LEO and GEO application.
Subsystem What is in-orbit experience with L Ion batteries
in GEO.

What is the fusing strategy ? where the fuses  See comment on the left.
are located (hopefully not inside each unit).
 Are the units and spacecraft subject to ESD  See comment on the left.
testing.
 C band. Three command receivers, 3 OMNI  Classical approach no major comments.
TC & R antennas in transfer and emergency, 3 TLM
Subsystem TX + 2 TWTA in redundancy. Bit rate 4096
bps.
Deployment  Solar array deployment and strategy for Just a comment.
Mechanisms deployment not addressed.
 Since there is no detailed schedule, the page  There is some doubts on the delivery date, but
134 is considered as the master schedule. maybe is not a concern for insurance brokers.

With a Kick Off Dec 2012 and a coupling  It will be useful to get a combined schedule to
expected in March 2015 (25 months after the verify that there is no conflict( human resources,
KO), and a a launch scheduled for Nov 2015 manufacturing facilities and test facilities)
some slippages are expected. between their programs
Project
 The 6 months for the single line flow seems  There is some doubts on the delivery date, but
Schedule reduced to a minimum difficult to accomplish maybe is not a concern for insurance brokers.
on this kind of spacecraft.
 Design review activities, and manufacturing  It is stated that several major reviews have been
monitoring activities. executed including teams (customer
representatives) which attended these review.
What are their approvals rights and can they
report on their conclusion to the insurance

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