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We demonstrate the creation of a large area of high-resolution (260 × 209 km2 at 1 m/pixel) DTM mosaic from the Lunar Reconnaissance Orbiter Camera (LROC) Narrow Angle Camera (NAC) images over the Chang'E-4 landing site at Von Kármán crater using an in-house deep learning-based 3D modelling system developed at University College London, called MADNet, trained with lunar orthorectified images and digital terrain models (DTMs). The resultant 1 m DTM mosaic is co-aligned with the Chang'E-2 (CE-2) and the Lunar Orbiter Laser Altimeter (LOLA)—SELenological and Engineering Explorer (SELENE) blended DTM product (SLDEM), providing high spatial and vertical congruence. In this paper, technical details are briefly discussed, along with visual and quantitative assessments of the resultant DTM mosaic product. The LROC NAC MADNet DTM mosaic was compared with three independent DTM datasets, and the mean differences and standard deviations are as follows: PDS photogrammetric DTM at 5 m grid-spacing had a mean difference of −0.019 ± 1.09 m, CE-2 DTM at 20 m had a mean difference of −0.048 ± 1.791 m, and SLDEM at 69 m had a mean difference of 0.577 ± 94.940 m. The resultant LROC NAC MADNet DTM mosaic, alongside a blended LROC NAC and CE-2 MADNet DTM mosaic and a separate LROC NAC, orthorectified image mosaic, are made publicly available via the ESA planetary science archive's guest storage facility. [ABSTRACT FROM AUTHOR]

The internal heat flow related to the Moon’s composition, interior structure, and evolution history is not well-constrained and understood on a global scale. Up to now, only two in situ heat flow experiments, Apollo 15 and 17 were deployed nearly 50 years ago. The measured high values of heat flow might be influenced by lateral heat at highland/mare boundaries and enhanced by heat production from radioactive elements enriched unit, and may also be disturbed by astronauts’ activities. In this study, we proposed a new method to retrieve heat flows at two permanently shadowed craters, Haworth and Shoemaker of the Moon’s south pole, from Chang’E-2 microwave radiometer data and Diviner observations. Our results show that the average heat flow is 4.9 ± 0.2 mW/m2. This provides a constraint for the bulk concentration of Thorium within the lunar south polar crust 656 ± 54 ppb, which helps us understand the Moon’s thermal evolution and differentiation.

Abstract Compared with other remote observations, brightness temperatures (T B) derived from microwave emission measurements provide a unique means to characterize the physical properties of the lunar surface. Using Chang'E-2 microwave radiometer data, we produced 12 global T B images of the lunar surface during a diurnal cycle with different local times separated by approximately 2 h. There are two types of remarkable T B units on the lunar surface, the "hot regions" occurring during the lunar day in the lunar Maria regions and the "microwave cold spots" occurring during the nighttime typically related to young craters. Compared with their surroundings, the hot regions are much warmer during the lunar day and slightly colder at night, while the microwave cold spots are much colder during the lunar night and slightly warmer in the daytime. Moreover, the T B heating and cooling rates of these two units are larger than others at the same average latitude where they are located during the lunar day, especially after sunrise and before sunset. The hot regions have a good agreement with the mare regions with high TiO 2 abundance. Besides, brightness temperatures in the lunar Maria correlate closely with their TiO 2 abundance. For most microwave cold spots, they agree with the young craters, and their brightness temperature distributions have a significant negative correlation with the lunar surface nighttime temperature and rock abundance. [ABSTRACT FROM AUTHOR]

The precise orbit determination of Chang'E-2 is the most important issue for successful mission and scientific applications, while the lunar gravity field model with big uncertainties 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 LP165P, SGM150J, 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 LP165P model has better orbit overlap performance than the SGM150J model for Chang'E-2100 km × 100 km orbit and the SGM150J model performs better for Chang'E-2100 km × 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.

The Chang’E-2 digital elevation model (DEM, named CE2TMap2015), which is the highest resolution DEM product in China, was released with global coverage of the lunar surface. A detailed geometric quality assessment of the product is desirable for wider applications by users. A novel procedure for evaluating DEM geometric quality, which investigates both the global geometric uncertainty and local gross errors, is proposed in this paper. First, the DEM was divided into regular blocks and matched with the reference DEM. Then, the characteristics of errors were investigated using the statistical information of the matched tie points. Next, the local outlier factor (LOF) algorithm was performed to locate the gross errors. In our experiment, CE2TMap2015 was evaluated using the proposed method, with SLDEM2015 as the reference DEM. The results show that there were widespread geometric inconsistencies with an area-weighted average of 183.1 m horizontally (with the standard deviation being 101.2 m) and 2.3 m vertically (with the standard deviation being 15.4 m). Gross errors were detected automatically and were excluded in the statistical analysis. The periodic errors were extracted in the frequency domain using a Fourier transform. Our research results provide instructional information for the utilization of CE2TMap2015 by world-wide users. The proposed method can be used in the assessment of other planetary DEMs.

The orbit accuracy of the Chang’E-2 (CE-2) lunar probe is one of the most critical factors for a seamless mosaic of the global lunar topographic map. During the production of the CE-2 global lunar topographic map, a maximum deviation of kilometers magnitude existed in the horizontal direction of homologous points between neighboring images, while the maximum height deviation of these points is up to several hundred meters. This phenomenon indicates that current orbit determination results of CE-2 cannot truly reflect the relative position relationship between probe and lunar surface features. Against this background, global adjustment using images of the moon should be carried out to solve this problem. In this paper, the influence of CE-2 current orbit accuracy on the production of a global lunar topographic map will be analyzed based on the introduction of CE-2 observation data, including images and orbit data. Additionally, key technologies and technical processes of global adjustment using CE-2 images with high-resolution and large amounts of data will be researched. Finally, orbit optimization of CE-2 after global adjustment is analyzed, as well as the accuracy of the CE-2 global lunar topographic map for validation verification. [ABSTRACT FROM AUTHOR]

The lunar probe, Chang’E-2, is the first one to successfully achieve both the transfer to Sun–Earth libration point orbit and the flyby of near-Earth asteroid Toutatis. This paper, taking the Chang’E-2’s asteroid flyby mission as an example, provides a method to design low-energy transfers from the libration point orbit to an asteroid. The method includes the analysis of transfer families and the design of optimal impulse transfers. Firstly, the one-impulse transfers are constructed by correcting the initial guesses, which are obtained by perturbing in the direction of unstable eigenvector. Secondly, the optimality of one-impulse transfers is analyzed and the optimal impulse transfers are built by using the primer vector theory. After optimization, the transfer families, including the slow and the fast transfers, are refined to be continuous and lower-cost transfers. The method proposed in this paper can be also used for designing transfers from an arbitrary Sun–Earth libration point orbit to a near-Earth asteroid in the Sun–Earth–Moon system. [ABSTRACT FROM AUTHOR]

China’s space probe Chang’E-2 began its asteroid exploration mission on April 15, 2012 and had been in space for 243 days before its encounter with Toutatis. With no onboard navigation equipment available, the navigation of CE-2 during its fly-by of the asteroid relied totally on ground-based Unified S-Band (USB) and Very Long Baseline Interferometry (VLBI) tracking data. The orbit determination of Toutatis was achieved by using a combination of optical measurements and radar ranging. On November 30, 2012, CE-2 was targeted at a destination that was 15 km away from the asteroid as it performed its third trajectory correction maneuver. Later orbit determination analysis showed that a correction residual was still present, which necessitated another maneuver on December 12. During the two maneuvers, ground-based navigation faced a challenge in terms of the orbit determination accuracy. With the optimization of our strategy, an accuracy of better than 15 km was finally achieved for the post-maneuver orbit solution. On December 13, CE-2 successfully passed by Toutatis and conducted continuous photographing of Toutatis during the entire process. An analysis of the images that were taken from the solar panel monitoring camera and the satellite attitude information demonstrates that the closest distance obtained between CE-2 and Toutatis (Toutatis’s surface) was 1.9 km, which is considerably better than the 30 km fly-by distance that we originally hoped based on the accuracies that we can obtain on the satellite and Toutatis’ orbits. [ABSTRACT FROM AUTHOR]

Chang’E-2 (CE-2) has firstly successfully achieved the exploring mission from lunar orbit to Sun–Earth L2 region. In this paper, we discuss the design problem of transfer trajectory and at the same time analyze the visible segment of Tracking, Telemetry & Control (TT&C) system for this mission. Firstly, the four-body problem of Sun–Earth–Moon and Spacecraft can be decoupled in two different three-body problems (Sun–Earth + Moon Restricted Three-Body Problems (RTBPs) and Earth–Moon ephemeris model). Then, the transfer trajectory segments in different model are computed, respectively, and patched by Poincaré sections. The full-flight trajectory including transfer trajectory from lunar orbit to Sun–Earth L2 region and target Lissajous orbit is obtained by the differential correction method. Finally, the visibility of TT&C system at the key time is analyzed. Actual execution of CE-2 extended mission shows that the trajectory design of CE-2 mission is feasible. [ABSTRACT FROM AUTHOR]

Abstract: This paper addresses lunar escape maneuvers of the first Chinese Sun–Earth L2 libration point mission by the CHANG'E-2 satellite, which is also the world's first satellite to reach the L2 point from a lunar orbit. The lunar escape maneuvers are heavily constrained by the remaining propellant and the condition of telemetry, track and command, among others. First, these constraints are analyzed and summarized to design a target L2 Lissajous orbit and an initial transfer trajectory. Second, the maneuver mathematical models are studied. The multilevel maneuver schemes which consist of phasing maneuvers and a final lunar escape maneuver are designed for actual operations. Based on the scheme analysis and comparison, the 2-maneuver scheme with a 5.3-h-period phasing orbit is ultimately selected. Finally, the mission status based on the scheme is presented and the control operation results are discussed in detail. The methodology in this paper is especially beneficial and applicable to a future multi-mission instance in the deep space exploration. [Copyright &y& Elsevier]

Highlights: [•] Three high degree lunar gravity field models are compared using various methods. [•] SGM150 is better for geophysical parameters inversion and orbit determination. [•] Localized spectrum can be used to judge the magnitude and depth of mascon. [Copyright &y& Elsevier]