Entity

Time filter

Source Type

Évry, France

De Chambure D.,European Space Agency | Guedron S.,French National Center for Space Studies | Aubin D.,ARIANESPACE
61st International Astronautical Congress 2010, IAC 2010 | Year: 2010

The ARIANE 5 ECA launcher is the European workhorse. The current version, dubbed 'PA-2' was successfully qualified in 2009 in a generic way by ASTRIUM in the frame of the ESA Ariane development programme PA-2. During the exploitation phase, ESA funds the so-called "level 1" post flight analysis, based on flight measurement, that provide very important information on the launcher behaviour and its functional parameters at stages and engines level. Beside these key information, some in-house analysis were performed at CNES and ESA but also at ASTRIUM, SNECMA and ARIANESPACE in order to identify some affordable improvement that could allow to increase the ARIANE 5 ECA launch vehicle performance. The status beginning of 2009 was sufficiently promising to initiate a project called 'A5ECA Performance Improvement Plan'. The given target was to achieve at least 10 T performance equivalent single launch for GTO mission, by end 2010, beginning 2011. With the Payload performance improvement plan achieved, ARIANESPACE will provide the adequate response to the new customer needs for the dual launch configuration, without any negative impact on the environment for the Payloads. This paper will address the current status and main results obtained. It will focus on the technical description of the most promising selected performance improvement tracks that will be qualified at launch system level. Among them are: - Interface Flange deletion at upper part level - Reduction of discrepancies for VULCAIN 2 and HM7B functional parameters based on post flight data analysis - Optimisation of the VULCAIN 2 and HM7B mixture ratio within the qualified domain - Improvement of the LH2 thermal residual mastering of the ESC-A upper stage - System constraints release The corresponding expected payload mass capacity will be given. Copyright © 2010 by GUEDRON & al. Source


Astorg J.-M.,French National Center for Space Studies | Jasinski M.,French National Center for Space Studies | Coulon D.,European Space Agency | Gerard B.,ARIANESPACE
61st International Astronautical Congress 2010, IAC 2010 | Year: 2010

The Soyuz at CSG program is approaching its end with the formal qualification of the Launch System to be pronounced at the beginning of 2011, before the start of the first commercial launch campaign. Therefore, this paper presents a summary of this ambitious development, the progress status in September 2010, the remaining activities and also the main difficulties encountered. First lessons learned are also discussed. Obviously, these lessons learned will be revisited after first launch and start of exploitation phase. Source


Roviera P.M.,European Space Agency | Bertrand J.,French National Center for Space Studies | Lardot C.,ARIANESPACE
13th International Conference on Space Operations, SpaceOps 2014 | Year: 2014

Ground segment is often considered as a secondary issue with respect to the flight segment, nevertheless a launch complex is a key element of a space system and gives a significant contribution to the success of a launch system and to its long-term sustainability. The launch complex reliability, availability and affordability are key elements to ensure access to space. While in the past the ground segment design tended to be only an outcome of the flight segment requirements, the new global and competitive context require that the launch system shall be considered as a whole. In particular, not only ground segment development costs but also its operational and long term global ownership costs have to be taken into account since the very first project trade-offs. Furthermore, the increasing demand for a more environmental conscious and sustainable development approach and the associated regulatory requirements shall be duly taken on board. This paper intends to give an overview of Ariane and other ESA launch complexes at Kourou, French Guiana, from the design concept to the operational success story return of experience, in view of future developments. Also specific aspects related to ESA launch vehicles manufacturing facilities and interfaces with the launch range will be dealt. Source


Thompson S.P.,ARIANESPACE | Andersson G.,RUAG Space Sweden | Davies W.,RUAG Space Switzerland | Plaza M.A.,Airbus
European Space Agency, (Special Publication) ESA SP | Year: 2012

On October 21st, 2011, lifting off from the ELS launch site in French Guiana, a Soyuz ST-B and FREGAT upper stage, carried the first two Galileo IOV spacecraft on a 3-hour 49-minute flight and successfully injected the 2 Galileo Navigation spacecraft into a circular medium-Earth orbit. The Dispenser System, the subject of this paper, is the equipped launch vehicle hardware mated directly to the FREGAT upper stage and built specifically to carry 2 Galileo IOV spacecraft during all ground and flight operations up to the moment of separation. The Dispenser System was purposely built for the Galileo IOV missions under European Space Agency and Arianespace contract. The prime contractor was selected to be RUAG Space in Sweden (Linköping) for all Dispenser "System and Management" activities and with subcontracts placed to RUAG Space in Switzerland (Zurich) for the Dispenser "Structure" and EADS CASA Spain (Madrid) for the "Hold Down and Release System" (HRS) hardware. The "Structure" is designed to transfer ground and flight loads between the spacecraft and the Launch Vehicle. The upper part, an aluminium sandwich box-type structure, interfaces with the satellites, whereas the lower part transitions to a lower frame, via a CFRP strut arrangement, to interface with the FREGAT upper stage. The spacecraft separation sub-system is composed of two sets of four low-shock "HRS" units and four "pushers" enabling to firmly hold the satellites during ground and flight operations and to release them when ordered by the Launch Vehicle. The Dispenser System also comprises an electrical sub-system and MLI. This paper summarises the overall Design, Development and Verification activities leading to the Qualification of the Dispenser System hardware. This will include the Structure and HRS contribution to the overall System Qualification. An overview of the System hardware will be described along with DDV logic, some key analysis performed and several of the full scale qualification tests achieved (at element and system level) leading to the pronouncement of qualification. Such tests being mechanical strength, stiffness, dynamic and functional. The latter for overall performance validation. Several of the results will be presented in accordance with defined specifications. In addition, the Dispenser System is equipped with telemetry instrumentation comprising 20 sensors. These sensors are dedicated to the monitoring of the flight environment in the vicinity of the spacecraft. The conclusions of the mechanical and thermal data obtained during the first flight are highlighted. Source


Kadzhaev V.,KBOM | Barmin I.,KBOM | Denoyers J.-Y.,ARIANESPACE | Ragot A.,French National Center for Space Studies
Acta Astronautica | Year: 2011

Some key aspects and criteria tasks for ensuring an acceptable reliability and safety level for complex technical systems are discussed in the view of successful operation of a launch complex, at the stage of Launch Vehicle (LV) preparation. The standards and principles of adequate characteristics for launch site core technological systems are defined. The tasks for evaluation the probability of faultless operation for the systems, their reliability a posteriori, and safety barriers formation are described. The model of the pre-launch phase is presented as a random process, in the form of "simple Poisson flow". © 2010 Elsevier Ltd. Source

Discover hidden collaborations