Rosetta Lander—After seven years of cruise, prepared for hibernation

Ulamec,; Stéphan,; Biele,; Jens,; Fantinati,; Cinzia,; Fronton,; Jean-François,; Gaudon,; Philippe,; Geurts,; Koen,; Krausé,; Mestres, Christian; Kuechemann,; Óliver,; Maibaum,; Michael, Cassia; Paetz,; Brigitte,; Roll,; Reinhard,; Willnecker,; Rainer,

doi:10.1016/j.actaastro.2012.06.020

Cited by 11 publications

(5 citation statements)

References 20 publications

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“…The Lander operations centres include a Lander telemetry and command system to support all dataprocessing and distribution tasks for system and experiment control, software for Lander operations planning purposes and data archiving hardware and software. At the LCC, a Lander Ground Reference Model (GRM), as well as a software simulator, are available for reference tests, validation of procedures and trouble-shooting tasks [6].…”

Section: Operations Conceptmentioning

confidence: 99%

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Rosetta Lander – Landing and operations on comet 67P/Churyumov–Gerasimenko

Ulamec¹,

Fantinati²,

Maibaum³

et al. 2016

Acta Astronautica

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Section: Operations Conceptmentioning

confidence: 99%

“…1 shows a drawing of the Rosetta Lander (Philae), Fig. 2 an image of the Flight Model during integration at ESTEC [6].…”

Section: Introductionmentioning

confidence: 99%

Rosetta Lander – Landing and operations on comet 67P/Churyumov–Gerasimenko

Ulamec¹,

Fantinati²,

Maibaum³

et al. 2016

Acta Astronautica

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“…During cruise the Lander has been attached to the Orbiter with the MSS (Mechanical Support System) which also includes the push-off device, separating PHILAE from the Orbiter. [48][108] [109] In this vantage position it was able to support ROSETTA during critical phases such as the Mars fly-by and while the comet was out of view of the boresighted mothership instruments (Fig. 2).…”

Section: Philae -Landed and Foundmentioning

confidence: 99%

Small spacecraft in small solar system body applications

Grundmann¹,

Meb²,

Biele

et al. 2017

2017 IEEE Aerospace Conference

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In the wake of the successful PHILAE landing on comet 67P/Churyumov-Gerasimenko and the launch of the first Mobile Asteroid Surface Scout, MASCOT, aboard the HAYABUSA2 space probe to asteroid (162173) Ryugu, small spacecraft in applications related to small solar system bodies have become a topic of increasing interest. Their unique combination of efficient capabilities, resource-friendly design and inherent robustness makes them attractive as a mission element at the frontiers of exploration of the solar system by larger spacecraft as well as stand-alone low-cost approaches to open up the solar system for a broader range of interests.The operators' requirements for cutting-edge missions compatible with available launch capabilities impose significant constraints in resources, timelines, timeliness, mass and size. To create spacecraft feasible within these constraints, the mission design teams need to accept a broad range of equipment maturity levels from fresh concepts to off-the-shelf units. The resulting Constraints-Driven Engineering (CDE) environment has led to new methods which transcend traditional evenly-paced and sequential development. We evolved and extended Concurrent Design and Engineering (CD/CE) methods originally incepted for intitial studies into Concurrent Assembly, Integration and Verification (CAIV). It is applied in all phases in most of our projects to achieve convergence of asynchronous subsystem maturity timelines and to match parallel tracks of integration and test campaigns. When facing such a challenge, Model-Based Systems Engineering (MBSE) supports design trades and constant configuration evolution due to unforeseen changes. Proactive change and schedule acceleration has resulted from systemlevel CD/CE optimization across interface boundaries by MBSE-aided CAIV.We discuss advantages and constraints of small spacecraft for planetary science and applications, focusing on emerging areas of activity such as planetary defence, on the background of our projects. These include the comet lander PHILAE flown aboard

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“…Rosetta was launched in 2004 and, after more than seven years of cruising, the spacecraft went into deep space hibernation in June 2011 [1]. Rosetta has been successfully reactivated in January 2014 as it approaches its target comet.…”

mentioning

confidence: 98%

Experimental Investigations of the Comet Lander Philae Touchdown Dynamics

Witte¹,

Schroeder²,

Kempe³

et al. 2014

Journal of Spacecraft and Rockets

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The comet lander Philae (as part of Europe's Rosetta mission) is en route to its target, 67/P ChuryumovGerasimenko. With landing operations coming up at the end of 2014, a partial retesting of the Philae lander's touchdown system was carried out in spring of 2013. Intensive testing was performed as part of Philae's design and verification program approximately 10 years ago. However, the new test series specifically addresses touchdown conditions that have been out of capability of the pendulum test facility used at those times. Thus, the follow-up tests focus on touchdown conditions such as asymmetric loads, effects from terrain undulation, and the effect of granular soil mechanics, which could not be studied sufficiently in the original tests. This paper provides insight into the touchdown system of the Philae lander, the characteristics of the used test facility, its weight offloading operating mode, and the specific application to a small-body landing test. The results of the study are presented and discussed in terms of their importance to the ongoing landing preparations. Nomenclature a = acceleration, m∕s 2 b = damping coefficient, N · s∕m d = rotary damping coefficient, Nms F = force, N g = Earth gravity I = inertia, kg · m 2 j = complex number k = stiffness, N∕m L = length, m m = mass, kg M = moment, N · m p, q, r = roll, pitch, and yaw angular rates, deg ∕s s = displacement, m v = velocity, m∕s δ = decay rate, 1∕s λ = eigenvalue, 1∕s σ = thread pitch, m Φ, Θ, and Ψ = roll, pitch, and yaw angles, deg ω = eigenfrequency, 1∕s, or angle, deg Subscripts B = body C = contact D = damper end = final value R = rotary S = surface TOS = test object suspension x, y, z = identifiers for coordinate axes 0 = initial value

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Rosetta Lander—After seven years of cruise, prepared for hibernation

Cited by 11 publications

References 20 publications

Rosetta Lander – Landing and operations on comet 67P/Churyumov–Gerasimenko

Rosetta Lander – Landing and operations on comet 67P/Churyumov–Gerasimenko

Small spacecraft in small solar system body applications

Experimental Investigations of the Comet Lander Philae Touchdown Dynamics

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