Spot 2 End-of-Life:  Disposal Maneuvers

Moussi, Aurelie; Pena, Xavier

doi:10.2514/6.2010-2276

Cited by 7 publications

(6 citation statements)

References 0 publications

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“…This ensures the equal treatment of the evolution of the hypothetical and the real state of the object. The propagator is a fully numerical, Runge-Kutta 7 (8) integrator with variable step-size taking into account perturbations from the geopotential (8 × 8), the atmosphere (NRLMSIS-00), the solar radiation pressure (modelled with conical Earth shadow) and the Moon and Sun third bodies.…”

Section: Propagation and Flux Analysismentioning

confidence: 99%

“…1), performing large manoeuvres out of the very congested region in the altitude band from 690 to 820 km. The SPOT satellites [7][8][9] achieve low individual relative reductions due to the fact that in this analysis they are predicted to remain in orbit for about 40 years or more after performing the EOL-manoeuvre. Landsat 4 [10], ERS-2 [11] and the Iridium satellites [12] achieve individual reduction rates of more than 80% in number of collisions.…”

Section: Pls In Leomentioning

confidence: 99%

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Impact of End-of-Life manoeuvres on the collision risk in protected regions

et al. 2017

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Section: Propagation and Flux Analysismentioning

confidence: 99%

Section: Pls In Leomentioning

confidence: 99%

Impact of End-of-Life manoeuvres on the collision risk in protected regions

et al. 2017

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“…Already during initial internal discussions on a deorbiting strategy in 2003 it was decided to choose a circular deposit orbit for ERS-2 instead of an elliptic one as for SPOT-2 deorbiting 6 . One reason was the fact that for a given perigee altitude, circular orbits result in lower lifetimes as demonstrated by ERS-2 simulations at ESOC.…”

Section: A Circular Versus Elliptic Orbitmentioning

confidence: 99%

“…+/-10%. The amount of hydrazine available closer to depletion was also estimated with the PVT Method (PV=nRT law for an assumed perfect gas 6 ). Maneuvers had to be scheduled and adjusted such as to exhaust this fuel, reaching the desired deposit orbit and reach fuel depletion in visibility of one of available ground stations.…”

Section: B Spacecraftmentioning

confidence: 99%

A Satellite Retires - The ERS-2 Deorbiting in Summer 2011

Diekmann¹,

Marc²,

Canela³

et al. 2012

SpaceOps 2012 Conference

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The ERS-2 deorbiting started on 6 th July 2011 after 16 years of successful operations of this ESA Earth Observation satellite. Many orbit lowering maneuvers were necessary to reach the target altitude of 570 km. Apart from the late failure of a backup gyro, which had no impact on the overall activity, all subsystems onboard performed perfectly. Although not originally foreseen in the early mission days, the later decision to deorbit ERS-2 was mostly compliant with international guidelines and ESA requirements on space debris mitigation and ensured a re-entry of the satellite in less than 25 years. The ERS-2 deorbiting was the first such activity of an ESA polar orbiting satellite. It was started with an initial re-orbiting in Feb 2011 in order to achieve a 3-days repeat cycle for scientific reasons for a period of 3 months. This orbit change served as a dress rehearsal for the later orbit lowering maneuvers and platform operations. The deorbiting related operations were implemented at ESA's Operations Centre ESOC in Darmstadt, Germany, in close collaboration with the Mission Management, the ESTEC based Post Launch Support Office and industrial support by ASTRIUM Toulouse. This included the definition of the overall operations concept, the maneuver strategy, on-board configuration trade-offs, contingency plans, new and modified procedures, extensive simulation and training sessions and an extended ground station network. This paper summarizes these activities together with the deorbiting background and objectives, timeline and results.

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“…CNES has already tested through its different EOL operations a few strategies 4,5 : several OCMs to decrease the perigee altitude after releasing the operational orbit, or an infinite-duration thrust after a few OCMs. Several items of interest have been highlighted.…”

Section: B Spaceflight Mechanicsmentioning

confidence: 99%

Disposal Operation Strategies for Remote Sensing Satellite Fleets in Nominal and Emergency Situations

Deguine¹,

Bertrand²,

Horblin³

et al. 2012

SpaceOps 2012 Conference

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Since December 2010, a new French Law on Space Operations (LSO) must be complied with by any entity related to space activities. It imposes, for instance, that any satellite operator shall demonstrate his capability to control the space vehicle, whatever the mission phase from the launch up to its End Of Life (EOL). The French Space Agency (CNES) is currently operating several remote sensing satellites (the last one called PLEIADES 1A), among a larger fleet of satellites. In that context, CNES has decided to perform several specific studies in order to define satellite disposal operation plans in any situation. The typical scenario of EOL operations consists in implementing five phases : disposal orbital manoeuvres, fluidic passivation, electrical passivation, transmitter disconnection and EOL orbit computation. One shall point out that these satellites (except PLEIADES 1A and 1B) were not originally designed to conform with the constraints imposed by the LSO. Thus, detailed analysis were conducted to identify the on-board and the on-ground improvements, as well as the operations chronology, without compromising in any way the security in the conduct of the operations. Depending on the context (nominal, contingency or emergency case) and the satellite subsystems status, different scenarios have been defined and compared in terms of strategy of disposal orbital manoeuvres, on-board and on-ground software upgrades, cumbersome operations, complexity, feedback… This paper addresses this tradeoff, and moreover, it focuses on two main points : 1) the on-board software upgrades (monitoring parameters, Failure Detection Isolation Recovery strategy, chronology and constraints of modifications upload) and the equipment that must be switched off or for which configuration parameters must be tuned, 2) the different disposal orbit manoeuvre strategies : several Orbit Control Manoeuvres (OCM), one or two OCMs followed by an infinite-duration thrust, or an unique infinite-duration thrust. In conclusion, the generic principles applied in these studies could be considered as guidelines for any other satellite platform EOL operations.

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Spot 2 End-of-Life: Disposal Maneuvers

Cited by 7 publications

References 0 publications

Impact of End-of-Life manoeuvres on the collision risk in protected regions

Impact of End-of-Life manoeuvres on the collision risk in protected regions

A Satellite Retires - The ERS-2 Deorbiting in Summer 2011

Disposal Operation Strategies for Remote Sensing Satellite Fleets in Nominal and Emergency Situations

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