1. Lunar Exploration Program and Space Engineering Center, Beijing 100190, China
2. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China
3. Dong Fang Hong Satellite Co. Ltd., Beijing 100084, China
4. Key Laboratory of Autonomous Navigation and Control for Deep Space Exploration, Ministry of Industry and Information Technology, Beijing 100081, China
Corresponding author (firstname.lastname@example.org)
Chang'E-IV will be the first soft-landing and rover mission on the lunar farside. The relay satellite, which is located near the Earth-Moon L2 point for relay communication, is the key to the landing mission. Based on an analysis of the characteristics of the task and the technical difficulties associated with the relay satellite system, the overall design scheme of the relay communication mission is proposed in terms of trajectory design and communication system design among other aspects. First, according to the complex dynamic environment, a mission orbit that serves as an uninterrupted communication link is presented. A short-duration and low-energy transfer trajectory with lunar flyby is discussed. Orbital correction and a low-cost control strategy for orbit maintenance in the Earth-Moon L2 point region are provided. Second, considering the existing technical constraints, the requirement of relay communication in different stages and the design schemes of frequency division and redundant relay communication system are introduced. Finally, based on the trajectory design index and the performance of the communication system, the overall design scheme of the relay communication mission is proposed. This mission will provide the technical support and reference required for the Chang'E-IV mission.
This work was supported by National Science and Technology Major Project of the Ministry of Science and Technology of China (Lunar Exploration Program), National Natural Science Foundation of China (Grant No. 11572038), and Chang Jiang Scholars Program.
(Color online) Geometric relationships of the Earth-Moon system, and distributions of libration points.
(Color online) Measurement and control of relay satellite and relay communication link.
(Color online) Relay satellite located in Earth-Moon L2 halo orbit, and communications for lunar farside.
(Color online) Orbital types near the libration point.
Halo orbit in the region of Earth-Moon L2.
(Color online) Direct transfer trajectory (LU: Earth-Moon distance).
(Color online) Transfer trajectory with lunar flyby.
(Color online) Flight trajectory of low-energy transfer via Sun-Earth L2 point (AU: Sun-Earth distance).
(Color online) Flight trajectory of low-energy transfer via Earth-Moon L1 point.
(Color online) Flight trajectory of low-energy transfer in three-body system.
(Color online) Flight sequence of lunar flyby transfer.
Flight trajectory of relay satellite for three years on Earth-Moon halo orbit.
(Color online) Expanded state of high-gain mesh parabolic antenna.
(Color online) Configuration of relay satellite for launch state.
(Color online) Configuration of relay satellite in orbit state.
(Color online) Schematic flight diagram of relay satellite.
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