Page 31 - test

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

DFH 4 Series Spacecraft Date : 28 Sept 2014
Page 29 of 38

9. CHINASAT 18 DFH-4E SPACECRAFT TECHNICAL ASSESSMENT MOST OF THE COMMENTS MADE
FOR CHINA 16 CAN BE REPEATED HERE. THE SATELLITE IS EVEN MORE COMPLEX.

CHINASAT 18 Observation Comment /Assessment Cri
 The customer is China Satellite  There are several TBD in the satellite mission
Communication (China Satcom). The (service life, launch date...). It means that the as
spacecraft is a DFH 4E type with a Ku , ka and of today the mission and configuration are not
Ka BSS payload. , Launch date Feb 2017, well defined. Therefore it is difficult to evaluate.
OML TBD. Bus 100 Volts, Li ion two
batteries with 60 cells. TBD
 The spacecraft. Mass: 5500 kg, dry mass 2276  Significant step in the power (around 15 kw)
Overview Kg Power: 15000 W TBC .
 Payload 6 antennas, 41 active transponders
 Module arrangement (service module and  Classical, central cylinder, U shape with N
payload) South and earth panel and antenna feed on the
top floor.
 Most of the hardware is under the  Just a comment
responsibility of CAST, some items are
subcontracted.
 Page 3. Provide the responsibility of each  He program manager of this very difficult
Chief, Manager, and Directors. Who is satellite is also the program manager of Chinasat
Team reporting whom? Who sign the specifications? 9A. It is not credible. The fact that they put such
Organization statement in their presentation induce a doubt on
every word they say !!
 Rockwell Collins RW, RWE, TBD  It seems that the entire payload is procured from
 Galileo IRES Thales Alenia Space.
Major  Thales Alenia Space ETCA PCU  In that case, it will be interesting to know what
Subcontractors  Thales Alenia Space Repeater, Earth deck are the requirements, or if it is a “what you see is
antenna, East west antenna, RF switches, other
what you get” approach.
payload products
 NTS, SSPA
 Ku 4 coverage beams, Ka band 14 users’ spots,
ka BSS mission 1 steerable beam., reflectors  Mission quite complex and innovative.
(4 deployable reflectors)
Ku Ka and  KU: LCTWTA (150 W) 20 for 18 and
LCTWTA (150 W) 14 for 12.
Ka BSS  Ka forward: LCTWTA radiative (140 W) 8 for
payload 7  Some clarifications will help..
 Ka return: LCTWTA radiative (130 W) 3 for 2
LCTWTA radiative (130 W) 3 for 2
 Ka BSS
 Antenna it is assumed that the antennas are
shaped.
Pointing accuracy ±0.1 , what about during  No comment at this stage
Design station keeping
EOL15a power margin: 7.6 % (7.5% specified )  Should be more specific (Solar array, batteries)
Characteristics (Partial channels back-off ) does it means that the traffic has to be reduced?

Table 10-a Chinasat 18 technical assessment

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