Perturbed motion of the artificial satellite of the Moon in the project «Ukrselena»

2009 ◽  
Vol 15 (1) ◽  
pp. 5-8
Author(s):  
Yu.V. Aleksandrov ◽  
1966 ◽  
Vol 25 ◽  
pp. 373
Author(s):  
Y. Kozai

The motion of an artificial satellite around the Moon is much more complicated than that around the Earth, since the shape of the Moon is a triaxial ellipsoid and the effect of the Earth on the motion is very important even for a very close satellite.The differential equations of motion of the satellite are written in canonical form of three degrees of freedom with time depending Hamiltonian. By eliminating short-periodic terms depending on the mean longitude of the satellite and by assuming that the Earth is moving on the lunar equator, however, the equations are reduced to those of two degrees of freedom with an energy integral.Since the mean motion of the Earth around the Moon is more rapid than the secular motion of the argument of pericentre of the satellite by a factor of one order, the terms depending on the longitude of the Earth can be eliminated, and the degree of freedom is reduced to one.Then the motion can be discussed by drawing equi-energy curves in two-dimensional space. According to these figures satellites with high inclination have large possibilities of falling down to the lunar surface even if the initial eccentricities are very small.The principal properties of the motion are not changed even if plausible values ofJ3andJ4of the Moon are included.This paper has been published in Publ. astr. Soc.Japan15, 301, 1963.


2020 ◽  
Vol 12 (1) ◽  
pp. 123
Author(s):  
Kai Wu ◽  
Ce Ji ◽  
Lei Luo ◽  
Xinyuan Wang

The observation of solid earth tides (SET) provides an important basis for understanding the structure of the earth’s interior, and has long been the focus of research in geoscience. However, actually, there still exist some limitations in capturing its global-scale information only with ground stations. Remote sensing technology can realize large-scale deformation monitoring of high point density constantly. However, it is still difficult for the artificial satellite system to meet the requirements of SET monitoring in terms of field of view and temporal resolution now. In this work, the moon is hypothesized as a new platform for SET observation combined with interferometric synthetic aperture radar (InSAR) technology. Based on the tidal model and lunar ephemeris, the spatial and temporal characteristics of the SET from the lunar view were analyzed. Furthermore, the calculations demonstrate that more abundant SET information can be observed in this view. After comparing various observation modes, the single-station with repeat-pass differential InSAR was selected for this simulation. We mainly considered the restriction of observation geometry on moon-based InSAR under three signal bandwidths, thereby providing a reference for the sensor design. The results demonstrate that the moon-based platform offers the potential to become an optimal SET observation method.


2009 ◽  
Vol 2009 ◽  
pp. 1-24 ◽  
Author(s):  
Jean Paulo dos Santos Carvalho ◽  
Rodolpho Vilhena de Moraes ◽  
Antônio Fernando Bertachini de Almeida Prado

Herein, we consider the problem of a lunar artificial satellite perturbed by the nonuniform distribution of mass of the Moon taking into account the oblateness (J2) and the equatorial ellipticity (sectorial termC22). Using Lie-Hori method up to the second order short-period terms of the Hamiltonian are eliminated. A study is done for the critical inclination in first and second order of the disturbing potential. Coupling terms due to the nonuniform distribution of mass of the Moon are analyzed. Numerical simulations are presented with the disturbing potential of first and second order is. It an approach for the behavior of the longitude of the ascending node of a near Sun-synchronous polar lunar orbit is presented.


2004 ◽  
Vol 1017 (1) ◽  
pp. 434-449 ◽  
Author(s):  
BERNARD DE SAEDELEER ◽  
JACQUES HENRARD

Author(s):  
Anne-Sophie Martin

Humans have always looked up at the stars and dreamed about outer space as the final frontier. The launch of the first artificial satellite—Sputnik—in 1957 by the Soviet Union and the first man on the Moon in 1969 represent significant missions in space exploration history. In 1972, Apollo 17 marked the last human program on the lunar surface. Nevertheless, several robotic spacecrafts have traveled to the Moon, such as the Soviet Luna 24 in 1976, and China’s Chang’e 4 in 2019, which was the first time a space vehicle touched down on the Moon’s far side. The international space community is currently assessing a return to the Moon in 2024 and even beyond, in the coming decades, toward the Red Planet, Mars. Robots and rovers (for example Curiosity, Philae, Rosetta, and Perseverance) will continue to play a major role in space exploration by paving the way for future long-duration missions on celestial bodies. It is still impossible to land humans on Mars or on other celestial bodies because there are significant challenges to overcome from technological and physiological perspectives. Therefore, the support of machines and artificial intelligence is essential for developing future deep space programs as well as to reach a sustainable space exploration. One can imagine a future scenario where robots and humans collaborate on the Moon’s surface or on celestial bodies to undertake scientific research, to extract and to analyze space resources for a possible in situ utilization, as well as to build sites for human habitation and work. The principles of free exploration and cooperation are core elements in the international space legal framework as mentioned in Article I of the 1967 Treaty on Principles Governing the Activities of States in the Exploration and Use of Outer Space, Including the Moon and Other Celestial Bodies. In this context of new ‘robots–humans’ cooperation, it is also necessary to consider the provisions of the 1972 Convention on the International Liability for Damage Caused by Space Objects, the 1975 Convention on Registration of Objects Launched into Outer Space, the 1968 Agreement of the Rescue of Astronauts, the Return of Astronauts and the Return of Objects Launched into Outer Space, and the 1979 Agreement Governing the Activities of States on the Moon and Other Celestial Bodies, as well as some recent international agreements signed for future Moon missions given their significant importance for space exploration.


2011 ◽  
Vol 2011 ◽  
pp. 1-19 ◽  
Author(s):  
Jean Paulo dos Santos Carvalho ◽  
Rodolpho Vilhena de Moraes ◽  
Antônio Fernando Bertachini de Almeida Prado

Low-altitude, near-polar orbits are very desirable as science orbits for missions to planetary satellites, such as the Earth's Moon. In this paper, we present an analytical theory with numerical simulations to study the orbital motion of lunar low-altitude artificial satellite. We consider the problem of an artificial satellite perturbed by the nonuniform distribution of the mass of the Moon (J2–J5,J7, andC22). The conditions to get frozen orbits are presented. Using an approach that considers the single-averaged problem, we found families of periodic orbits for the problem of an orbiter travelling around the Moon, where frozen orbits valid for long periods of time are found. A comparison between the models for the zonal and tesseral harmonics coefficients is presented.


Author(s):  
E.S. Gordienko ◽  
A.V. Simonov ◽  
P.A. Khudorozhkov

The paper discusses the design of a mission for delivering lunar soil to the Earth. The analysis of its main stages is carried out. These stages include possible flight pattern selection, analysis of the flight from the Earth to the circular orbit of the Moon artificial satellite, determination of trajectories of removal from lunar surface into the reference orbit, the search for return paths that depart from the Moon and fall into a given area on the Earth’s surface. A variant of determining the initial approximation for the method of return paths constructing is proposed. It is based on solving a two-parameter boundary value problem in the central field of the Earth. Varying the duration of the flight from the Moon to the Earth and the time of the spacecraft approach to the Earth, pointing return trajectory into vicinity of the polygon P is achieved for a given perigee radius. The article presents the main characteristics of the mission obtained using this technique.


Author(s):  
A.V. BAGROV ◽  
A.O. DMITRIEV ◽  
V.A. LEONOV ◽  
I.V. MOSKATINYEV ◽  
V.K. SYSOEV ◽  
...  

The paper discusses the problem of developing an optical system for global positioning on the Moon to within one meter designed to service a limited number of users. It was demonstrated that the optimal solution of the problem would be to continuously monitor the positions of laser light beacons on the lunar surface from on-board an artificial satellite of the Moon equipped with an onboard TV camera, as well as from onboard a spacecraft placed at the L1 and L2 Lagrange points of the Earth-Moon system. The paper demonstrates the feasibility of a global lunar optical navigation and communications system based on space systems projects that are being developed at NPO Lavochkin: Spektr-UV observatory, lunar spacecraft Luna-25 and Luna-26. The use of these space systems will make it possible to start working in realistic terms on the navigation/communications system as a part of the future engineering infrastructure for lunar exploration. Keywords: telescope, optical navigation system, lunar base, Lagrange point, Spektr-UV, Luna-25, Luna-26.


1966 ◽  
Vol 25 ◽  
pp. 363-371
Author(s):  
P. Sconzo

In this paper an orbit computation program for artificial satellites is presented. This program is operational and it has already been used to compute the orbits of several satellites.After an introductory discussion on the subject of artificial satellite orbit computations, the features of this program are thoroughly explained. In order to achieve the representation of the orbital elements over short intervals of time a drag-free perturbation theory coupled with a differential correction procedure is used, while the long range behavior is obtained empirically. The empirical treatment of the non-gravitational effects upon the satellite motion seems to be very satisfactory. Numerical analysis procedures supporting this treatment and experience gained in using our program are also objects of discussion.


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