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Yu. K. Zaiko

Bio: Yu. K. Zaiko is an academic researcher from Unitary enterprise. The author has contributed to research in topics: Trajectory & Moon landing. The author has an hindex of 2, co-authored 2 publications receiving 5 citations.

Papers
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Journal ArticleDOI
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.

5 citations

Journal ArticleDOI
TL;DR: In this paper, basic concepts and algorithms laid as foundations of the scheme of landing on the Martian moon Phobos (developed for the Phobos-Grunt project) are presented.
Abstract: Basic concepts and algorithms laid as foundations of the scheme of landing on the Martian moon Phobos (developed for the Phobos-Grunt project) are presented. The conditions ensuring the landing are discussed. Algorithms of onboard navigation and control are described. The equations of spacecraft motion with respect to Phobos are considered, as well as their use for correction of the spacecraft motion. The algorithm of estimation of the spacecraft’s state vector using measurements with a laser altimeter and Doppler meter of velocity and distance is presented. A system for modeling the landing with a firmware complex including a prototype of the onboard computer is described.

2 citations


Cited by
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Journal ArticleDOI
Yue Wang1, Xiaojie Wu1
TL;DR: In this article, a dynamical model was developed in the body-fixed frame of Phobos, in which the high-precision gravity field and exact physical libration of phobos, the gravity of Mars with J2, and the gravity perturbations of the Sun, Jupiter, and Earth are considered.
Abstract: A dynamical model is developed in the body-fixed frame of Phobos, in which the high-precision gravity field and exact physical libration of Phobos, the gravity of Mars with J2, and the gravity perturbations of the Sun, Jupiter, and Earth are considered. The JPL development ephemeris are applied to calculate the positions of celestial bodies. Phobos is considered as a homogeneous polyhedron with 16 037 vertices to characterize its irregular shape and the corresponding gravity field. The physical libration of Phobos is incorporated into its rotational motion by using the results in ‘Report of the IAU WGCCRE’. With the proposed model, equivalent gravity and slope on Phobos surface are calculated and analysed. The liftoff velocity is also computed and presented. Besides, the orbital environment is also investigated. Instantaneous equilibrium points in the Mars–Phobos system are computed and demonstrated, and the acceleration of a particle in the vicinity of Phobos is analysed to find out the main influencing factor in different regions. Quasi-satellite orbits and libration point orbits, which were determined in the circular restricted three-body problem model, are simulated in different dynamical models. The results applying the newly developed high-fidelity dynamical model have shown significant differences with respect to existing models, suggesting that dynamical models with higher accuracy are needed for close-range orbital activities.

8 citations

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.
01 Jan 2013
TL;DR: In this paper, a first-order solution on the osculating elements is obtained with the use of perturbation theories and validation is performed using the numerical model as comparison term.
Abstract: In this thesis, quasi-satellite orbits in the elliptic restricted three-body problem are studied from a preliminary mission design point of view. A description of such orbits and their long-term evolution is given, and the stability conditions investigated are used for the case of the Mars-Phobos system. A first-order solution on the osculating elements is obtained with the use of perturbation theories and validation is performed using the numerical model as comparison term. A trajectory design algorithm is developed using the obtained analytical solutions with the purpose of studying different approach strategies to the Martian moon. An energy consumption analysis is performed to understand which strategy is more efficient in terms of fuel consumption. Due to the approximations made, the obtained analytical solutions have low validity when in close proximity to Phobos, as a result a control procedure is introduced onto the trajectory algorithm, which performs timely corrections to the actual trajectory. Two landing scenarios are considered providing some flexibility in terms of mission design. Keywords—Quasi-Satellite Orbits, Elliptic Restricted Three-Body Problem, Variation of Parameters, Differential Evolution, MarsPhobos System.