The geometric accuracy of topographic mapping with high-resolution remote sensing images is inevita-bly affected by the orbiter attitude jitter.Therefore,it is necessary to conduct preliminary research on the stereo m...The geometric accuracy of topographic mapping with high-resolution remote sensing images is inevita-bly affected by the orbiter attitude jitter.Therefore,it is necessary to conduct preliminary research on the stereo mapping camera equipped on lunar orbiter before launching.In this work,an imaging simulation method consid-ering the attitude jitter is presented.The impact analysis of different attitude jitter on terrain undulation is conduct-ed by simulating jitter at three attitude angles,respectively.The proposed simulation method is based on the rigor-ous sensor model,using the lunar digital elevation model(DEM)and orthoimage as reference data.The orbit and attitude of the lunar stereo mapping camera are simulated while considering the attitude jitter.Two-dimensional simulated stereo images are generated according to the position and attitude of the orbiter in a given orbit.Experi-mental analyses were conducted by the DEM with the simulated stereo image.The simulation imaging results demonstrate that the proposed method can ensure imaging efficiency without losing the accuracy of topographic mapping.The effect of attitude jitter on the stereo mapping accuracy of the simulated images was analyzed through a DEM comparison.展开更多
Asteroid exploration trajectories which start from a lunar orbit are investigated in this work.It is assumed that the probe departs from lunar orbit and returns to the vicinity of Earth,then escapes from the Earth by ...Asteroid exploration trajectories which start from a lunar orbit are investigated in this work.It is assumed that the probe departs from lunar orbit and returns to the vicinity of Earth,then escapes from the Earth by performing a perigee maneuver.A low-energy transfer in Sun-EarthMoon system is adopted.First,the feasible region of lowenergy transfer from lunar orbit to perigee within 5 000 km height above the Earth surface in Sun-Earth-Moon system is calculated and analyzed.Three transfer types are found,i.e.,large maneuver and fast transfers,small maneuver and fast transfers,and disordered and slow transfers.Most of feasibility trajectories belong to the first two types.Then,the lowenergy trajectory leg from lunar orbit to perigee and a heliocentric trajectory leg from perigee to asteroid are patched by a perigee maneuver.The optimal full-transfer trajectory is obtained by exploiting the differential evolution algorithm.Finally,taking 4179 Toutatis asteroid as the target,some low-energy transfer trajectories are obtained and analyzed.展开更多
Chang'E-1 lunar Orbiter was launched by Long March 3A rocket from Xichang Satel-lite Launch Center at 18:05BT(Beijing Time) Oct.24,2007.It is the first step of its ambitious three-stage moon program,a new mileston...Chang'E-1 lunar Orbiter was launched by Long March 3A rocket from Xichang Satel-lite Launch Center at 18:05BT(Beijing Time) Oct.24,2007.It is the first step of its ambitious three-stage moon program,a new milestone in the Chinese space exploration history.The primary science objectives of Chang'E-1 lunar orbiter are to obtain three-Dimension(3D) stereo images of the lunar surface,to analyze the distribution and abundance of elements on the surface,to investigate the thickness of lunar soil,evaluate helium-3 resources and other characteristics,and to detect the space environment around the moon.To achieve the above four mission objectives,eight sets of scientific instruments are chosen as the payloads of the lunar orbiter,including a CCD stereo camera(CCD),a Sagnac-based interferometer spectrometer(ⅡM),a Laser Altimeter(LAM),a Microwave Radiometer(MRM),a Gamma-Ray Spectrometer(GRS),an X-ray spectrometer(XRS),a High-Energy Particle Detector(HPD),and two Solar Wind Ion Detectors(SWID).The detected data of the payloads show that all payloads work well.This paper introduces the status of payloads in the first phase and preliminary scientific results.展开更多
The lifetime of a lunar satellite orbit is constrained by the non-spherical nature of the Moon’s gravity field. The orbital lifetime of lunar orbits depends significantly on the initial conditions of the orbit. Right...The lifetime of a lunar satellite orbit is constrained by the non-spherical nature of the Moon’s gravity field. The orbital lifetime of lunar orbits depends significantly on the initial conditions of the orbit. Right ascension of ascending node (Ω) is one of the important orbital parameter affecting the orbital lifetime. In the present work we have analyzed the effect of Ω on the variation of lifetime with altitude for circular lunar orbits. It is found that at a particular initial altitude, a small increase in the altitude results in substantial increase in the orbital lifetime due to effect of the long periodic terms of Earth’s gravity on eccentricity and this transition altitude is different for different Ω. Further, it is observed that the variation of transition altitude with Ω follows a definite, but different trend for orbits with different inclinations. The transition altitude for polar orbits is found to be higher without the effect of Sun and Earth gravity. Variation of transition altitude with orbital inclination is also analyzed. Lifetimes of high altitude circular lunar orbits are analyzed and it is observed that at high altitudes lifetime decreases with altitude.展开更多
Orbits that are frozen in an averaged model,including the effect of a disturbing body laying on the equatorial plane of the primary body and the influence of the oblateness of the primary body,have been applied to pro...Orbits that are frozen in an averaged model,including the effect of a disturbing body laying on the equatorial plane of the primary body and the influence of the oblateness of the primary body,have been applied to probes orbiting the Moon.In this scenario,the main disturbing body is represented by the Earth,which is characterized by a certain obliquity with respect to the equatorial plane of the Moon.As a consequence of this,and of the perturbing effects that are not included in the averaged model,such solutions are not perfectly frozen.However,the orbit eccentricity,inclination,and argument of pericenter present limited variations and can be set to guarantee the fulfillment of requirements useful for lunar telecommunication missions and navigation services.Taking advantage of this,a practical case of a Moon-based mission was investigated to propose useful solutions for potential near-future applications.展开更多
The precise orbit determination of ChanE-2 is the most important issue for successful mission and scientific applications, while the lunar gravity field model with big un- certainties has large effect on Chang＇E-2 or...The precise orbit determination of ChanE-2 is the most important issue for successful mission and scientific applications, while the lunar gravity field model with big un- certainties has large effect on Chang＇E-2 orbit determination. Recently, several new gravity models have been produced using the latest lunar satellites tracking data, such as LP16SP, SGM1SOJ, GL0900D and GRGM900C. In this paper, the four gravity models mentioned above were evaluated through the power spectra analysis, admittance and coherence analysis. Effect of four lunar gravity models on Chang＇E-2 orbit determination performance is investigated and assessed using Very Long Baseline Interferometry （VLBI） tracking data. The overlap orbit analysis, the posteriori data residual, and the orbit prediction are used to evaluate the orbit precision between successive arcs. The LPI65P model has better orbit overlap performance than the SGM150J model for Chang＇E-2100 km x 100 km orbit and the SGM150J model performs better for Chang＇E-2100 km x 15 km orbit, while GL0900D and GRGM900C have the best orbit overlap results for the two types of Chang＇E-2 orbit. For the orbit prediction, GRGM900C has the best orbit prediction performance in the four models.展开更多
According to the history of lunar detection, the relationship between selenodesy and lunar detection is reviewed , and the focus of the lunar detection and the lunar detection plan of China are summarized. The key tec...According to the history of lunar detection, the relationship between selenodesy and lunar detection is reviewed , and the focus of the lunar detection and the lunar detection plan of China are summarized. The key techniques of selenodesy are presented, and the applications of selenodesy to the lunar detection are discussed.展开更多
The lunar-landing is the continuity of manned spaceflight engineering. Comparing with the manned spacecraft engineering, it requires more reliability , larger scale, and more funds. On the basis of China’s achievemen...The lunar-landing is the continuity of manned spaceflight engineering. Comparing with the manned spacecraft engineering, it requires more reliability , larger scale, and more funds. On the basis of China’s achievements and the experiences of foreign countries, the paper brings forward the idea that using the existing transportation technology to send the launch vehicles and cosmonauts to the near-earth orbit in batches, assembling the components together on the space-launch platform, and then launching them to the moon to fulfill our dream of manned landing on the moon. The paper also discusses the space launch platform and the launching ways.展开更多
基金Supported by the National Natural Science Foundation of China(42221002,42171432)Shanghai Municipal Science and Technology Major Project(2021SHZDZX0100)the Fundamental Research Funds for the Central Universities.
文摘The geometric accuracy of topographic mapping with high-resolution remote sensing images is inevita-bly affected by the orbiter attitude jitter.Therefore,it is necessary to conduct preliminary research on the stereo mapping camera equipped on lunar orbiter before launching.In this work,an imaging simulation method consid-ering the attitude jitter is presented.The impact analysis of different attitude jitter on terrain undulation is conduct-ed by simulating jitter at three attitude angles,respectively.The proposed simulation method is based on the rigor-ous sensor model,using the lunar digital elevation model(DEM)and orthoimage as reference data.The orbit and attitude of the lunar stereo mapping camera are simulated while considering the attitude jitter.Two-dimensional simulated stereo images are generated according to the position and attitude of the orbiter in a given orbit.Experi-mental analyses were conducted by the DEM with the simulated stereo image.The simulation imaging results demonstrate that the proposed method can ensure imaging efficiency without losing the accuracy of topographic mapping.The effect of attitude jitter on the stereo mapping accuracy of the simulated images was analyzed through a DEM comparison.
基金supported by the National Basic Research Programof China(973 Program)(2012CB720000)the National Natural Science Foundation of China(11102020)+1 种基金Program for New Century Excellent Talents in UniversityBeijing Higher Education Young Elite Teacher Project and China Scholarship Council
文摘Asteroid exploration trajectories which start from a lunar orbit are investigated in this work.It is assumed that the probe departs from lunar orbit and returns to the vicinity of Earth,then escapes from the Earth by performing a perigee maneuver.A low-energy transfer in Sun-EarthMoon system is adopted.First,the feasible region of lowenergy transfer from lunar orbit to perigee within 5 000 km height above the Earth surface in Sun-Earth-Moon system is calculated and analyzed.Three transfer types are found,i.e.,large maneuver and fast transfers,small maneuver and fast transfers,and disordered and slow transfers.Most of feasibility trajectories belong to the first two types.Then,the lowenergy trajectory leg from lunar orbit to perigee and a heliocentric trajectory leg from perigee to asteroid are patched by a perigee maneuver.The optimal full-transfer trajectory is obtained by exploiting the differential evolution algorithm.Finally,taking 4179 Toutatis asteroid as the target,some low-energy transfer trajectories are obtained and analyzed.
文摘Chang'E-1 lunar Orbiter was launched by Long March 3A rocket from Xichang Satel-lite Launch Center at 18:05BT(Beijing Time) Oct.24,2007.It is the first step of its ambitious three-stage moon program,a new milestone in the Chinese space exploration history.The primary science objectives of Chang'E-1 lunar orbiter are to obtain three-Dimension(3D) stereo images of the lunar surface,to analyze the distribution and abundance of elements on the surface,to investigate the thickness of lunar soil,evaluate helium-3 resources and other characteristics,and to detect the space environment around the moon.To achieve the above four mission objectives,eight sets of scientific instruments are chosen as the payloads of the lunar orbiter,including a CCD stereo camera(CCD),a Sagnac-based interferometer spectrometer(ⅡM),a Laser Altimeter(LAM),a Microwave Radiometer(MRM),a Gamma-Ray Spectrometer(GRS),an X-ray spectrometer(XRS),a High-Energy Particle Detector(HPD),and two Solar Wind Ion Detectors(SWID).The detected data of the payloads show that all payloads work well.This paper introduces the status of payloads in the first phase and preliminary scientific results.
文摘The lifetime of a lunar satellite orbit is constrained by the non-spherical nature of the Moon’s gravity field. The orbital lifetime of lunar orbits depends significantly on the initial conditions of the orbit. Right ascension of ascending node (Ω) is one of the important orbital parameter affecting the orbital lifetime. In the present work we have analyzed the effect of Ω on the variation of lifetime with altitude for circular lunar orbits. It is found that at a particular initial altitude, a small increase in the altitude results in substantial increase in the orbital lifetime due to effect of the long periodic terms of Earth’s gravity on eccentricity and this transition altitude is different for different Ω. Further, it is observed that the variation of transition altitude with Ω follows a definite, but different trend for orbits with different inclinations. The transition altitude for polar orbits is found to be higher without the effect of Sun and Earth gravity. Variation of transition altitude with orbital inclination is also analyzed. Lifetimes of high altitude circular lunar orbits are analyzed and it is observed that at high altitudes lifetime decreases with altitude.
基金M.Cinelli was supported by the G4S_2.0 project,developed under the auspices of the Italian Space Agency(ASI)within the framework of the Bando Premiale CICOT-2018-085the co-participation of the Italian Institute for Astrophysics(INAF)and the Politecnico di Torino(POLITO).
文摘Orbits that are frozen in an averaged model,including the effect of a disturbing body laying on the equatorial plane of the primary body and the influence of the oblateness of the primary body,have been applied to probes orbiting the Moon.In this scenario,the main disturbing body is represented by the Earth,which is characterized by a certain obliquity with respect to the equatorial plane of the Moon.As a consequence of this,and of the perturbing effects that are not included in the averaged model,such solutions are not perfectly frozen.However,the orbit eccentricity,inclination,and argument of pericenter present limited variations and can be set to guarantee the fulfillment of requirements useful for lunar telecommunication missions and navigation services.Taking advantage of this,a practical case of a Moon-based mission was investigated to propose useful solutions for potential near-future applications.
基金funded by National Natural Science Foundation of China(41374012)
文摘The precise orbit determination of ChanE-2 is the most important issue for successful mission and scientific applications, while the lunar gravity field model with big un- certainties has large effect on Chang＇E-2 orbit determination. Recently, several new gravity models have been produced using the latest lunar satellites tracking data, such as LP16SP, SGM1SOJ, GL0900D and GRGM900C. In this paper, the four gravity models mentioned above were evaluated through the power spectra analysis, admittance and coherence analysis. Effect of four lunar gravity models on Chang＇E-2 orbit determination performance is investigated and assessed using Very Long Baseline Interferometry （VLBI） tracking data. The overlap orbit analysis, the posteriori data residual, and the orbit prediction are used to evaluate the orbit precision between successive arcs. The LPI65P model has better orbit overlap performance than the SGM150J model for Chang＇E-2100 km x 100 km orbit and the SGM150J model performs better for Chang＇E-2100 km x 15 km orbit, while GL0900D and GRGM900C have the best orbit overlap results for the two types of Chang＇E-2 orbit. For the orbit prediction, GRGM900C has the best orbit prediction performance in the four models.
基金Funded by the National 973 Programof China (No.2006CB701301) the Basic Research of Geomatics and Geodesy of the Key Laboratory of Geo-space Environment and Geodesy, Ministry of Education, China (No.03-04-10) .
文摘According to the history of lunar detection, the relationship between selenodesy and lunar detection is reviewed , and the focus of the lunar detection and the lunar detection plan of China are summarized. The key techniques of selenodesy are presented, and the applications of selenodesy to the lunar detection are discussed.
文摘The lunar-landing is the continuity of manned spaceflight engineering. Comparing with the manned spacecraft engineering, it requires more reliability , larger scale, and more funds. On the basis of China’s achievements and the experiences of foreign countries, the paper brings forward the idea that using the existing transportation technology to send the launch vehicles and cosmonauts to the near-earth orbit in batches, assembling the components together on the space-launch platform, and then launching them to the moon to fulfill our dream of manned landing on the moon. The paper also discusses the space launch platform and the launching ways.
