May 2022, Volume 2 Issue 2

    

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• Review

  Technology Roadmap for Chang'E Program

  PEI Zhaoyu, WANG Qiong, TIAN Yaosi

  2015, 2(2): 99-110. https://doi.org/10.15982/j.issn.2095-7777.2015.02.001

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  The moon is the nearest celestial body of the earth. Because of its unique spatial position and broad prospects of scientific exploration, it has become the preferred objective and consecutive option of human space exploration and resource utilization. In this paper, at first the development and accomplishments of the world's major space powers on lunar exploration are retrospected, and their future development plans are summarized. Then the development idea and technology roadmaps for the Chinese Lunar Exploration Program are introduced in details. Finally future development direction of Chinese lunar exploration is analyzed and a concept of robotic lunar science station mission before 2030 is proposed.
• Review

  Review and Prospect of the Powered Descent Guidance and Control Technologies for Lunar Soft Landing

  LI Shuang, TAO Ting, JIANG Xiuqiang, ZHANG Shuyu, ZHOU Jie

  2015, 2(2): 111-119. https://doi.org/10.15982/j.issn.2095-7777.2015.02.002

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  Future lunar landing missions substantially focus on lunar resources and moon base, which lead to high-precision requirements for landing on the moon. And to achieve safe pin-point landing at a pre-selected landing site, the powered descent guidance and control technologies are of great importance for these missions. First, in this paper, two successful lunar soft landing scenarios and corresponding guidance modes are summarized systematically. Second, the existing lunar soft-landing guidance schemes and state-of-art are specifically described and comparatively analyzed. Finally, taking future sample return and moon base missions for potential project goals, a comprehensive analysis and prospect for next generation powered descent guidance and control technologies and the related core scientific and technological problems for lunar soft landing are conducted.
• Article

  Application of Interferometric Tracking by China DSN in CE-3 Soft Landing

  HAN Songtao, TANG Geshi, CAO Jianfeng, CHEN Lue, REN Tianpeng, WANG Mei

  2015, 2(2): 120-124. https://doi.org/10.15982/j.issn.2095-7777.2015.02.003

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  This paper discussed the possibility of application of Interferometric tracking to track CE'3 during Soft Landing by China Deep Space Network. Algorithm of adaptive model reconstruction and interferometric phase unwrapping are discussed in details, which can avoid accuracy of predict orbit deteriorate caused by spacecraft maneuver and can keep interferometric phase continuous. Based on data analysis in project, the accuracy of the interferometric tracking is in the order of 0.3ns, which corresponds to 30nrad angular accuracy.
• Article

  Sensitivity Analysis of Initial Error for the Trajectory to the Sun-Earth Libration Point

  WANG Yamin, QIAO Dong, CUI Pingyuan

  2015, 2(2): 125-130. https://doi.org/10.15982/j.issn.2095-7777.2015.02.004

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  The sensitivity of initial error for the transfer trajectory from lunar orbit to the Sun-Earth libration point orbit was calculated and analyzed. First, the short and long transfer trajectories for this kind of transfer issue were proposed. Then, the mathematical relation between initial error and terminal derivation was built. The relation is found to be linear by numerical calculation. Finally, the reason why the linear relation existed and its applicable conditions were explored by the first-order variation expression of initial error and terminal derivation. The result indicated that the long transfer is more sensitive to initial error than short transfer and that the applicable conditions for long transfer is stricter.
• Article

  High-Frequency Impact Handheld Sampling Device for Astronaut

  CHEN Huazhi, JIANG Shengyuan, ZHANG Ming, ZHANG Yuliang, SHEN Yi, QUAN Qiquan, LIANG Lu, ZHANG Zhixian

  2015, 2(2): 131-136. https://doi.org/10.15982/j.issn.2095-7777.2015.02.005

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  Obtaining primary lunar regolith with bedding information is one of the important targets in China's lunar-landing and manual sampling project. A high-frequency impact handheld sampling device suitable for astronauts is designed comparing with foreign sampling techniques. The sampling device uses particle's single-direction motion in high-frequency impact, which can keep sample's primary bedding information, reduce power consumption, and increase coring ratio. Particle's single-direction moving effect and coring ratio will be increased through anisotropic friction morphology on coring mechanism surface meanwhile. Law of coring ratio affected by impact frequency and surface morphology has been obtained via variable frequency coring experiment, which can be technical reference for the design of manual sampling device in China's lunar landing project.
• Article

  Drag-Based Nonlinear Predictive Guidance Law for Mars Entry

  ZHAO Zhenhua, YANG Jun, LI Shihua, GUO Lei

  2015, 2(2): 137-143. https://doi.org/10.15982/j.issn.2095-7777.2015.02.006

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  Aiming at precision landing of Mars entry for Mars exploration mission, this paper proposes a novel drag-based nonlinear predictive guidance law. Taking into account the aerodynamical parameters perturbation of Mars vehicle, the air density parameter perturbation of Mars, external disturbance and initial states errors, a nonlinear predictive guidance law based on optimization theory is designed for the three-dimensional Mars entry model. The simulation results indicate that under the proposed guidance law, the Mars vehicle achieves a precision landing with the control constraint being satisfied.
• Article

  Spacecraft Doppler Tracking with Possible Violations of LLI and LPI: Preliminary Bounds on LLI from Mars Express

  ZHANG Yufei, LIU Jinghao, HUANG Yong, XIE Yi

  2015, 2(2): 144-148. https://doi.org/10.15982/j.issn.2095-7777.2015.02.007

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  Three-way spacecraft Doppler tracking is currently widely used and it plays an important role in the control and navigation of deep space missions. Using the theory of three-way Doppler tracking, including possible violations of the local Lorentz invariance (LLI) and the local position invariance (LPI), we analyzed the post-fit residuals of three-way Doppler tracking data of Mars Express. These Doppler observations were carried out from August 7th to 8th in 2009, with an uplink station administered by the European Space Agency at New Norcia in Australia and three downlink stations at Shanghai, Kunming and Urumqi in China. We find that, although these observations impose preliminary bounds on LLI at the level of 10^-2, they are not suitable for testing LPI because of the configuration of these stations and the accuracy of the observations. To our knowledge, this is one of the first attempts in China to apply radio science to the field of fundamental physics.
• Article

  Lyapunov-Based Hazard Avoidance Control Method for Landing on Small Celestial Bodies

  HU Haijing, ZHU Shengying, CUI Pingyuan

  2015, 2(2): 149-154. https://doi.org/10.15982/j.issn.2095-7777.2015.02.008

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  Aiming at the difficulty in designing the coupled attitude and orbit control lander, the lyapunov-based hazard avoidance control method for landing on small celestial bodies is presented. Firstly, the dynamic model is given, and the is selected based on the current potential of the lander and the threat from the hazards. Then, the on-off logic of the thrusters is derived according to the Lyapunov theory. This guarantees that the lander can arrive at the landing site and avoid the hazards, and this process. Since the control logic is analytical, this control method can meet the real-time requirement of hazard avoidance and is easy to be applied in the engineering. The simulation results show that this method can avoid the hazards effectively and stabilize the attitude.
• Article

  Dynamic Surface Robust Guidance and Control for Landing on Asteroids

  ZHENG Yiyu, CUI Hutao, WANG Xiaofang

  2015, 2(2): 155-161. https://doi.org/10.15982/j.issn.2095-7777.2015.02.009

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  With a comprehensive application of the theory of the disturbance observer based (DOB) control and dynamic surface control, this paper develops a dynamic surface robust guidance method for precise landing on asteroids. A reference trajectory is first generated by using the spacecraft initial conditions and the terminal landing constraints. We consider the gravitational field modeling errors of the asteroid, parameter perturbations of the spacecraft, and external disturbances as a lumped disturbance of the dynamic system and then design a reference trajectory tracking controller using the DOB technique and dynamic surface control theory. We analyze the asymptotic convergence problem of the estimation of the lumped disturbance. We also present the stability analysis of the closed-loop reference trajectory tracking control system and develop a method to determine the controller parameters. Numerical simulation results show that the DOB designed in this paper can estimate the lumped disturbance effectively and that the closed-loop reference trajectory tracking control system has a fine stability and control precision.
• Article

  Asteroid Soft Landing Control Method based on Fuzzy Optimization Parameters

  WANG Qianqian, XIE Mujun, LI Yuanchun

  2015, 2(2): 162-167. https://doi.org/10.15982/j.issn.2095-7777.2015.02.010

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  In order to solve the shaking of sliding mode control based on conventional exponent trending law, a new sliding mode controller based on variable rate trending law is designed. Based on the dynamic model of an asteroid soft landing control system, the structure of sliding mode control based on conventional exponent trending law is deduced. Through analyzing the distance of moving point and sliding mode surface, a fuzzy optimization parameters strategy based on dynamic adjustment switch gain is used, which realizes speeding up the response speed and enhancing the system capacity of overcoming the perturbation and external disturbance when the moving point is far away from the sliding mode surface and eliminating chattering when the moving point is close to the sliding mode surface. The simulation results based on MATLAB show that the sliding mode controller based on variable rate trending law not only guarantees the rapidity of movement, but reduces the shaking of system, thus it has a good stability.
• Article

  Application Scheme of Ion Electric Propulsion System for Main-Belt Asteroid Sample and Return Mission

  YANG Fuquan, ZHAO Yide, LI Juan, GENG Hai, ZHANG Tianping, ZHOU Haiyan

  2015, 2(2): 168-173. https://doi.org/10.15982/j.issn.2095-7777.2015.02.011

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  Due to the ion electric propulsion high specific impulse feature, the launch weight of the spacecraft will be greatly reduced under the same payload to implement the orbit maneuver of an asteroid exploration. The application of ion electric propulsion in deep space exploration is investigated in this paper. On the basis of the successful experience of foreign countries and the analysis of the requirements of the task, the scheme and application strategy of the ion electric propulsion system are designed, and its thrust,specific impulse, propellant weight and power are calculated for the main-belt asteroid exploring spacecraft to meet the present life level of ion thruster. The research results show that the developing ion thruster can meet the requirements of the main-belt asteroid exploration mission and have reference value for the design of the spacecraft.
• Article

  Double Spectrum Camera Designed for Asteroid Detecting

  WANG Feng, YANG Bo, HU Cunming, WU Hao, FEI Xiaoxing

  2015, 2(2): 174-179. https://doi.org/10.15982/j.issn.2095-7777.2015.02.012

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  Based on DSP+FPGA configuration, a small and light-weight double spectrum camera is designed by adopting absolute perspective optics system, uncooled infrared sensor and CMOS sensor. It images both by infrared and visible light, can be used as prototype of optics sensor for asteroid detecting. It also can be used as optics payload of small satellites. This paper sets up the technique index system of double spectrum camera, discusses its components and working principle, expatiates its optics system and electronic design, and introduces the research overview of the prototype.
• Article

  Dispatchable Processing Method of Resource Constraint in Spacecraft Mission Planning

  CHEN Dexiang, XU Wenming, DU Zhiyuan, XU Rui

  2015, 2(2): 180-185. https://doi.org/10.15982/j.issn.2095-7777.2015.02.013

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  Considering the uncertainty and disturbance of environment in deep space exploration, spacecraft need to use mission planning technology to realize autonomous control. When a spacecraft applies the planning algorithm in aerospace engineering actirities, the time constraints and resource constraints should be considered. By analyzing the relationship between resource constraints, the dispatchable processing method of reusable resources in the execution of planning and the standard to determine whether resource value is dispatchable are proposed. Through the spacecraft simulation example, the dispatchable processing method of reusable resource in planning implementation is demonstrated to be valid.
• Article

  The Trial of Probing Gravitation with Spacecraft Doppler Tracking: (I) Modeling

  DENG Xuemei, XIE Yi

  2015, 2(2): 186-191. https://doi.org/10.15982/j.issn.2095-7777.2015.02.014

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  Currently two-way and three-way spacecraft Doppler tracking techniques are widely used and play important roles in control and navigation of deep space missions. Starting from a one-way Doppler model, we extend the theory to two-way and three-way Doppler models by making them include possible violations of the local Lorentz invariance (LLI) and the local position invariance (LPI) in order to test the Einstein equivalence principle, which is the cornerstone of general relativity and all other metric theories of gravity. After taking the finite speed of light into account, which is the so-called light time solution (LTS), we make these models depend on the time of reception of the signal only for practical convenience. We find that possible violations of LLI and LPI cannot affect two-way Doppler tracking under a linear approximation of LTS, although this approximation is sufficiently good for most cases in the solar system. We also know that, given the accuracy of measurement and control in China and no additional payload in this method, possible violations of LLI and LPI could be the scientific goals of Chinese measurement and control.
• Review for the First Meeting of the First Editorial Board of Journal of Deep Space Exploration

  2015, 2(2): 192-192. https://doi.org/10.15982/j.issn.2095-7777.2015.02.015

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