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Journal ArticleDOI

A robust guidance algorithm for the moon landing

26 Nov 2013-Cosmic Research (Springer US)-Vol. 51, Iss: 6, pp 465-477
TL;DR: An integrated conceptual basis is used to develop multistep terminal algorithms for guidance for the three segments of the descent of a landing module designed for the Moon landing.
Abstract: The paper deals with a choice of the rational trajectory of motion of a landing module designed for the Moon landing, from the moment of its de-orbiting from the near-lunar orbit up to landing. An integrated conceptual basis is used to develop multistep terminal algorithms for guidance for the three segments of the descent.
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Journal ArticleDOI
TL;DR: For the descent from the pericenter of a prelanding circumlunar orbit a comparison of three algorithms for the control of lander motion is performed.
Abstract: For the descent from the pericenter of a prelanding circumlunar orbit a comparison of three algorithms for the control of lander motion is performed. These algorithms use various combinations of terminal and programmed control in a trajectory including three parts: main braking, precision braking, and descent with constant velocity. In the first approximation, autonomous navigational measurements are taken into account and an estimate of the disturbances generated by movement of the fuel in the tanks was obtained. Estimates of the accuracy for landing placement, fuel consumption, and performance of the conditions for safe lunar landing are obtained.

3 citations

Journal ArticleDOI
TL;DR: In this article, an algorithm was developed for terminal guidance during the main deceleration section of the lunar landing trajectory of a spacecraft with an integrated propulsion system, which has a main engine with variable thrust and four auxiliary nonthrottleable engines.
Abstract: An algorithm is developed for terminal guidance during the main deceleration section of the lunar landing trajectory of a spacecraft with an integrated propulsion system, which has a main engine with variable thrust and four auxiliary nonthrottleable engines. A method of guidance adaptation to the actual motion conditions by measuring the thrust acceleration with jumps in time is proposed.
Journal ArticleDOI
TL;DR: In this paper, a direct method for optimizing the spatial trajectories of lunar landing in the deceleration phase with a limitation along the descent profile, when the lander must remain inside a certain cone with apex at a given landing point, is presented.
Abstract: A direct method for optimizing the spatial trajectories of lunar landing in the deceleration phase with a limitation along the descent profile, when the lander must remain inside a certain cone with apex at a given landing point, is presented. The model of motion is a point of variable mass moving in a uniform gravitational field. The method uses a two-level optimization of the characteristic velocity for a given distance and lateral displacement at free landing time. The upper level corresponds to one-dimensional nonlinear optimization of the landing time. The lower level corresponds to optimization for the landing times established at the upper level and the given coordinates of the landing point using discrete sets of pseudopulses and high-dimensional linear programming. Energetically accessible regions and regions when redetermining the landing point are presented as examples.