The ESA Lunar Lander Mission

Fisackerly, R.; Pradier, A.; Gardini, B.; Houdou, B.; Philippe, Christian; Rosa, Diego de la

doi:10.2514/6.2011-7217

Cited by 18 publications

(5 citation statements)

References 2 publications

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“…Overall, the system attains a good performance despite of the uncertainties. The dimensions of the obtained 3σ ellipse are comparable to a possible lander footprint (Fisackerly et al, 2011), giving to the system hazard avoidance capabilities.…”

Section: Conditionsupporting

confidence: 48%

“…Originally planned for launch in 2018 and designed for landing near the Moon's south pole, the mission's primary objectives include the demonstration of safe precision landing technology as part of preparations for participation to future human exploration of the Moon (Fisackerly et al, 2011). Recently, the project was put on hold at the 2012 ESA Ministerial Council, but the technology developed in the context of Lunar Lander phase B1 could be exploited for future cooperations in the area of Lunar Exploration with Russia.…”

Section: Planetary Landing Application Testmentioning

confidence: 99%

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A semi-analytical guidance algorithm for autonomous landing

Lunghi¹,

Lavagna²,

Armellín³

2015

Advances in Space Research

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One of the main challenges posed by the next space systems generation is the high level of autonomy they will require. Hazard Detection and Avoidance is a key technology in this context. An adaptive guidance algorithm for landing that updates the trajectory to the surface by means of an optimal control problem solving is here presented. A semi-analytical approach is proposed. The trajectory is expressed in a polynomial form of minimum order to satisfy a set of boundary constraints derived from initial and final states and attitude requirements. By imposing boundary conditions, a fully determined guidance profile is obtained, function of a restricted set of parameters. The guidance computation is reduced to the determination of these parameters in order to satisfy path constraints and other additional constraints not implicitly satisfied by the polynomial formulation. The algorithm is applied to two different scenarios, a lunar landing and an asteroidal landing, to highlight its general validity. verify the versatility of the algorithm in realistic cases, by the introduction of attitude control systems, thrust modulation, and navigation errors. The proposed approach proved to be flexible and accurate, granting a precision of a few meters at touchdown.

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Section: Conditionsupporting

confidence: 48%

Section: Planetary Landing Application Testmentioning

confidence: 99%

A semi-analytical guidance algorithm for autonomous landing

Lunghi¹,

Lavagna²,

Armellín³

2015

Advances in Space Research

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“…To give a picture of a landing sequence and the phase considered here, a reference based on the ESA Lunar Lander scenario is drawn up. 8 This scenario is based on the heritage of previous missions, most notably Apollo, 9 and the terms introduced Secondhere are thus common terminology and applicable to typical landings on atmosphereless bodies of sufficient gravity. 10 Based on this, the guidance problem can be formulated mathematically.…”

Section: Area Of Studymentioning

confidence: 99%

Guidance for Autonomous Precision Landing on Atmosphereless Bodies

Gerth

Mooij

2014

AIAA Guidance, Navigation, and Control Conference

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Two key technologies that will likely fly on next-generation planetary landers are hazard detection and avoidance (HDA) and vision-based navigation. The purpose of HDA is to make previously unsafe landing sites accessible by future vehicles, and to increase the safe landing probability overall. Vision-based navigation will enable to target specific landing sites more precisely and also plays an important role for HDA. This paper formulates requirements on the guidance system that derive from the needs of these new systems. After the introduction of a reference mission scenario with HDA and vision-based navigation inthe-loop, an extensive literature survey of the state-of-the-art in approach-phase guidancealgorithms is presented. This presents the methods under the angle of HDA-compatibility. The sheer number of papers mentioned here leads to the conclusion that trade-offs are challenging. It is recommended to do a down-selection from the papers presented here, and do a performance-based trade study for the particular test case under consideration with a few candidates. As an example, E-Guidance is presented for a Mercury-and a Moon-landing scenario. Because the results differ dramatically, it is concluded that it is essential to perform trade-offs on the actual mission scenario under study, and that trades cannot merely be based on references in the literature. Because the proposed E-Guidance method is not satisfyingly robust, it is a goal for future research to improve upon this.

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“…Guidance, Navigation and Control (GNC) is a key enabling system for the mission and is responsible for assuring Sun pointing and burn execution during the Orbital segment and delivering the lander to a desired landing site on the Moon. Several recent papers have given an overview of GNC design for precision robotic lunar landers [1][2] [3]. To increase the probability of success, some of the key features that landers have incorporated in new designs are Vision Based Absolute Navigation [4], Hazard Avoidance Algorithms in Terminal Descent [5] and Terrain Relative Navigation [6] through an advanced sensor suite.…”

Section: Introductionmentioning

confidence: 99%

Overview of Guidance, Navigation and Control System of the TeamIndus lunar lander

Vatsal,

Barath,

Yogeshwaran

et al. 2019

Preprint

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TeamIndus' Lunar Logistics vision includes multiple lunar missions to meet requirements of science, commercial and efforts towards global exploration. The first mission is slated for launch in 2020. The prime objective is to demonstrate autonomous precision lunar landing, and Surface Exploration Rover to collect data on the vicinity of the landing site. TeamIndus has developed various technologies towards lowering the access barrier to the lunar surface.This paper shall provide an overview of design of lander GNC system.The design of the GNC system has been described after concluding studies on sensor and actuator configurations. Frugal design approach is followed in the selection of GNC hardware. The paper describes the constraints for the orbital maneuvers and lunar descent strategy.Various aspects of the GNC design of autonomous lunar descent maneuver -time line of events, guidance, inertial and optical terrain relative navigation schemes are described. The GNC software description focuses on system architecture, modes of operation, and core elements of the GNC software. The GNC algorithms have been validated using Monte-Carlo simulations and processor-in-loop testing. The paper concludes with a summary of key risk mitigation studies for soft landing.

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The ESA Lunar Lander Mission

Cited by 18 publications

References 2 publications

A semi-analytical guidance algorithm for autonomous landing

A semi-analytical guidance algorithm for autonomous landing

Guidance for Autonomous Precision Landing on Atmosphereless Bodies

Overview of Guidance, Navigation and Control System of the TeamIndus lunar lander

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