Apollo lunar descent guidance

Klumpp, Allan R.

doi:10.1016/0005-1098(74)90019-3

Cited by 202 publications

(82 citation statements)

References 3 publications

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“…During the terminal descent phase, forward and lateral velocity components were nulled out, and the altitude rate of the lunar module was controlled until touchdown [5].…”

Section: Historical Perspectivementioning

confidence: 99%

Lunar Descent Using Sequential Engine Shutdown

Springmann

2006

AIAA/AAS Astrodynamics Specialist Conference and Exhibit

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“…During the terminal descent phase, forward and lateral velocity components were nulled out, and the altitude rate of the lunar module was controlled until touchdown [5].…”

Section: Historical Perspectivementioning

confidence: 99%

Lunar Descent Using Sequential Engine Shutdown

Springmann

2006

AIAA/AAS Astrodynamics Specialist Conference and Exhibit

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“…The common objective of planetary landing guidance algorithms of previous studies is to precisely land on the predetermined landing site with minimum fuel consumption [1][2][3][4][5]. This implies that those algorithms are not suitable to figure out the maximum downrange of the lunar lander under fuel limits.…”

Section: Introductionmentioning

confidence: 99%

Lunar Lander Landing Site Decision in Low-Fuel Case

Seo

Hong

Tahk

2016

MATEC Web of Conferences

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Abstract. This paper deals with lunar landing site decision algorithms for the case when the lunar lander is not able to reach the original landing site. A new landing site which minimizes the fuel consumption of the lunar rover is determined from landing site candidates located within the maximum reachable downrange of the lunar lander. A path planning algorithm is introduced to determine the new landing site which has the shortest path to the original landing site among the candidates. Numerical simulations are conducted to verify the performance of the proposed algorithm.

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“…A trajectory based on a quartic polynomial in time, with no optimization involved, was used during the Apollo missions (Klumpp, 1974). A derivative of the Apollo lunar descent guidance has been still considered in recent years for the Mars Science Laboratory (MSL) (Wong et al, 2002).…”

Section: Introductionmentioning

confidence: 99%

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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Apollo lunar descent guidance

Cited by 202 publications

References 3 publications

Lunar Descent Using Sequential Engine Shutdown

Lunar Descent Using Sequential Engine Shutdown

Lunar Lander Landing Site Decision in Low-Fuel Case

A semi-analytical guidance algorithm for autonomous landing

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