Page 26 - test

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

DFH 4 Series Spacecraft Date : 28 Sept 2014
Page 24 of 38

CHINASAT 16 Observation Comment /Assessment Cri
minor modification and that therefore the equipment
could be considered as being “category D” is not
acceptable as such.
 Complex deployment system (2 reflectors on each
side) . How they will verify trough test that the
design is OK.
 ADPM is also a critical unit. How work the RF
sensing proposed
 The antenna testing should be developed.

 This is supposed to be an experimental payload  Service life more than one year ?
with interface protections.. But it will make the  Are they using hi Rel devices and EEE parts for this
Piggyback Laser satellite more complex, more difficult to application.
develop and may induce failure mode
communication detrimental for the main mission. The China 16  Is there any risk of failure propagation to the Ka
band AOCD or DHE subsystem or failure
is by itself sufficiently complex without adding propagation via the 1553 bus.
further complexity to this satellite.
 Pointing accuracy ±0.1, what about during  The spot beam size is 0.08°. It is said page 7 that
station keeping the pointing accuracy is 0.06°.they say better than
0.1° page 33. How these numbers are compatible by
Design themselves?_. It seems that they make use of RF
sensing. . Lack of in orbit reference for this critical
Characteristics system
EOL15a power margin: 7.6 % (7.5% specified )  Should be more specific (Solar array, batteries) does
(3.5 dB Output back-off ) it means that the traffic has to be reduced?

 Mass budget,  EPS, mass is 450 KG, what is behind this colossal
number?
 Propellant budget, no comment
 No comment at this stage,
 Power budget,.  The output power from the PCU is more than 7.8
KW. The ETCA PCU that we know and which has
been qualified is limited to 5/6 KW. It will be
useful to get a clear statement of this PCU
System manufacturer its qualification encompass the China
budgets 16 needs
 What is the worst case DoD
 TCR Link budget, no comment  No comment at this stage
 Antenna pointing accuracy, no comment  See above
 Reliability, 0.701 end of life, seems optimistic  No comment at this stage
with the TWT redundancy proposed.
 SPF list (page 52), seems incomplete, many  Should be updated ASAP in order to identify the
other SPF can be added. risk items.
 Page 56-95. According to the presentation half  Without going into details there several “new
of the hardware is categorized as category C developments” usage of Li Ion batteries, Ion
Thrusters, TPAM (to orient the ion thrusters, several
units repackaged in a single box, Xenon feeding
system. Xenon regulator, PPU, TSU, Ka receiver,
Qualification ADPME ..., It is difficult to understand why a unit is
status Category C with a status Flight proven, since the
unit is subject to significant changes.
 There is no mention of life test.
 Is the environment for the previous qualification
(Vibe, thermal, radiations...) encompassing the
Chinasat 16 needs.

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