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The objective of this project is to provide an optimized short time solution for small-medium size satellites, involving ITAR free solutions, as much as possible with regard to competitiveness and schedule, making extensive re-use of SPACEBUS product line heritage and flight records. 
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The fields covered by this study are: overall layout, structure, thermal control, propulsion, solar arrays, attitude control and command control (TDU i.e. Telecommand Decryption Unit ).
click for larger image | The current situation of industrial overcapacity leads THALES ALENIA SPACE to improve the SPACEBUS family coverage and extend its ITAR free capability to the lower range. | SPACEBUS 4000B2 is the lowest configuration belonging to the SPACEBUS family as presented below. 
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The following table presents the SB4000 B2 options/capabilities.
The medium range refers to first application program, the majority of the market target is anticipated to use 4000B2 "high" range. 
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(*) with use of radiative TWTA
(**) with AsGa solar cells on one panel per wing The SPACEBUS 4000B2 architecture is based on two main modules: 
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- The Service Module (SM) : structured around a central tube and standing main functions as propulsion, avionics and power supply.
- The Communication Module (CM) including repeater and TTC-RF
- Antennas are installed on East and West sides and on Earth deck panel.
- Avionic 4000 with Li-Ion batteries, 100V bus, Command control design around a central computer and modular distribution (power and data) units , Solar arrays for 100V bus and AsGa compatibility.
- Bi-propellant propulsion with enhanced 400N engine, up to 1900kg propellant tanks and 2 x 51 liter Helium tanks
- Primary structure is the SB3000B2 with high heritage
SB4000 avionic block diagram 
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Propulsion System Architecture 
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Structure SB4000 B2
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This project is full of synergies/parallels to both the SPACEBUS Product Line entity and one SB4000B2 under contract. This particular organization has been selected to fulfil Thales Alenia Space efficiency exigencies due to the fact that this contract corresponds to the first SB4000B2 ever built. Obviously, the project plan has been worked out to fit ESA and the first SB4000B2 on-going program in terms of time constraints. Major milestones are: - Kick Off in December 19th Dec 2006
- Baseline Design Review (BDR) on 5th Feb 2007
- Mid Term review (MTR) 3rd, 4th July 2007
- Final Review (FR) in November 2007
The project addresses the competitiveness of the platform SB4000B2 through two main ways: - Implementing the highly performing Avionic 4000 concept and solar array design, including ITAR-free solutions,
- Maximizing payload capabilities.
The main activities are to rearrange: - The SM ( Service Module) versus Avionic 4000 including additional European items,
- The CM (Communication Module) lay-out mainly to displace the PLDIU (PayLoad Distribution Interface Unit) from CM to the SM Internal Deck. This allows more dissipative area on CM for additional communication channels.
The project will allow Thales Alenia Space to keep the leadership in this capability range of satellite, and to compete with non-occidental prime constructors (i.e. China, Russia, India, etc). Beyond this, it will contribute to maintaining and improving SPACEBUS platform excellence and competitiveness.
- KO meeting 19th Dec 2006,
- BDR meeting held on 5th Feb 2007,
- MTR held on 3rd and 4th July 2007. All main issues are considered to be in a satisfactory condition.
Last Update: 23 Jul 2008
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