May 2022, Volume 5 Issue 4
    

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  • Continuous Propulsion Dynamics in very Far Space Exploration and Analysis of the Stuhlinger’s Solution
    LUAN Enjie
    2018, 5(4): 301-322. https://doi.org/10.15982/j.issn.2095-7777.2018.04.001
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    The exploration of the very far space in solar system will be a main target of the next phase of deep space exploration activities. The achievement of this goal relies on the breakthrough of the continuous propulsion power technology. Basing on the description of the Stuhlinger’s solution for spaceflight under continuous constant thrust, the relationships between the key parameters such as the payload ratio, mission time and flight distance of the very far space missions and the engine performance are analyzed . The conditions that the engine specific impulse and power need to satisfy and their effects on the payload ratio and the final flight speed are given under specific mission duration and specific flight distance requirements. In addition, the large elliptical transfer orbit and its transfer energy requirement of planetary exploration in solar system are derived under the two-body orbital dynamics, and the key technical indicators involved in the continuous thrust solar sail mission are theoretically calculated. These conclusions are the summerized by the basic theory of continuous propulsion scheme in deep space exploration, which can provide important inspiration and guidance for China’s future deep space activities.
  • Development of Deep Space Propulsion Technology
    LI Yong, DING Fenglin, ZHOU Cheng
    2018, 5(4): 323-330. https://doi.org/10.15982/j.issn.2095-7777.2018.04.002
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    Propulsion technology is an important factor restricting the deep space exploration capability. With the characteristics of the spacecraft for deep space exploration and the different project requirements, the requirements forthe propulsion concept are also diversity. The specifications, such as the thrust, specific impulse, power, and weight should be balanced. The present state and perspectives of the several types of propulsion technologies for deep space exploration project are introduced, such as hybrid model propulsion technology, solar energy electric propulsion technology, space nuclear electric propulsion technology (NEP), and sail propulsion technology, providing reference for the development of the deep space propulsion technology in China.
  • Research Progress of Plasma Magnetic Fluid Power Generation
    HUANG Hulin, LI Linyong, LI lai, LIU Feibiao
    2018, 5(4): 331-346. https://doi.org/10.15982/j.issn.2095-7777.2018.04.003
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    The working principle and power generation process of a plasma magnetohydrodynamic power generation system （MHDPG）is introduced，and the hot topics and key problems in the current research of MHDPG are analyzed. The research results and research progress are reviewed from both numerical simulation and experimental are analyzed investigations. It is believed that the MHDPG will be paid more and more attention，and will promote the development of aerospace technology.
  • Study on the Electric Propulsion System for Asteroid Detection
    LI Zongliang, GAO Jun, LIU Guoxi, ZHOU Cheng, TANG Zhangyang, ZOU Daren
    2018, 5(4): 347-353. https://doi.org/10.15982/j.issn.2095-7777.2018.04.004
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    The electric propulsion has the characteristics of high specific impulse, long service life and highly autonomous cruise, which will significantly reduce the propellant mass and improve the load ratio when it’s used for orbit maneuver operation during the cruise phase of asteroid detection. The electric propulsion system for asteroid detection is investigated. According to the mission requirements of the asteroid detection to the electric propulsion and the technical basis of the existing electric thruster, five kinds of electric propulsion system solutions are proposed and compared, the optimal solution is designed and the key technologies are analyzed.
  • Development and Prospect of Magnetically Shielded Hall Thruster
    XU Yanan, KANG Xiaolu, YU Shuilin
    2018, 5(4): 354-360. https://doi.org/10.15982/j.issn.2095-7777.2018.04.005
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    The magnetically shielded Hall thruster technology is the most influential innovation and breakthrough in the field of Hall propulsion in recent years. It is of great significance for expanding the application of Hall thrusters and improving the lifespan of the thruster. In this paper，the principle，and the characteristics of the magnetically shielded Hall thruster are introduced. The research status of the Hall thruster magnetic shielding is presented in terms of its proposition and verification，magnetic shielding technology of different power magnitude Hall thrusters，thermal design sensitivity of background pressure，and oscillation mode conversion. The future development of magnetically shielded Hall thruster technology is prospected.
  • Specific Mass Optimization Modeling of Space Nuclear Electric Propulsion System for Jupiter Exploration Mission
    ZHOU Cheng, WU Yanlong, WEI Yanming, LI Yong, WANG Ge, CONG Yuntian, SUN Kun, WANG Lei
    2018, 5(4): 361-366. https://doi.org/10.15982/j.issn.2095-7777.2018.04.006
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    The space nuclear electric propulsion (NEP) system is a revolutionary space propulsion technology that converts nuclear heat energy into electrical energy and drives high-power electric thrusters to generate thrust. Compared with traditional propulsion technology, NEP has the advantages of high specific impulse, high power and long life, which is very suitable for large-scale deep space exploration missions in the future. In this paper, the specific mass model of high power NEP system is established based on NEP system composition and the theory of small thrust orbit to obtain the maximum payload ratio. The complex coupling relation of orbit time, specific mass, power and payload ratio of NEP spacecraft can be decoupled by this model, which provides a computational basis for task optimization. The model was used to evaluate the technical specifications of the NEP system to complete the NASA Juno space mission. The calculation shows that when the specific mass of the NEP system reaches 4.8kg/kWe, it can the ground transfer time of the Juno space mission from 2266 days to 665 days, and the payload from 160kg to 1179kg, which greatly improves the spacecraft's detection capability and providing a useful reference for subsequent design.
  • Study on High Power All-Electric Propulsion System for Spacecraft Orbit Transfer
    TANG Zhangyang, ZHOU Cheng, HAN Dong, MA Xue, CHEN Tao
    2018, 5(4): 367-373. https://doi.org/10.15982/j.issn.2095-7777.2018.04.007
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    Compared with chemical propulsion，the application electric propulsion system in spacecraft can save the amount of propellant，which is able to significantly reduce the launch mass or allow more payloads to the target. In this paper，the research on high power electric thrusters in the world is investigated. An electric propulsion systemis designed for the near-earth spacecraft orbit transfer. Several schemes are compared with different thruster performances. At last，the suggestions are proposed for developing high power electric thruster and propulsion system in China.
  • Prospect of Lunar Base Construction Scheme
    YUAN Yong, ZHAO Chen, HU Zhenyu
    2018, 5(4): 374-381. https://doi.org/10.15982/j.issn.2095-7777.2018.04.008
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    With the further development of lunar exploration，the construction of lunar base is taken by many lunar exploration schemes and lunar development plans at home and abroad as an important goal. The lunar base will serve the future unmanned lunar exploration and manned lunar missions. The function and significance of the lunar base are analyzed. According to the carrying capacity of China’s rockets，a scheme for the lunar base construction is put forward，which includes the preliminary concept of the location constraint，the construction steps and the implementation process of the lunar base. The typical detection station and devices of the lunar base are analyzed. Some key problems of the lunar base are discussed，which will provide reference for the construction of the lunar base in the future.
  • Juno Radio Open Loop Measurement Experiment based on China’s Deep Space Stations
    CHEN Lue, PING Jinsong, LI Wenxiao, HAN Songtao, LIU Qing, CHEN Yongqiang, ZHANG Jianhui, JIAN Nianchuan
    2018, 5(4): 382-386. https://doi.org/10.15982/j.issn.2095-7777.2018.04.009
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    The construction of China’s deep space network supports China’s deep space missions，such as explorations of Lunar，Mars，Small planets，Jupiter，and etc. To validate China’s deep space network performance and obtain the radio measurement raw data，dozens of radio open loop measurement experiments of Juno which is one of Jupiter’s probe on orbit were accomplished. These open loop measurement experiments are the first time conducted by the China’s deep space stations tracking a in-orbit probe in Earth-Jupiter distance. VLBI terminate sampling and recording facilities were utilized to record Juno’s raw carrier signal，which was processed to extract Doppler frequency between Juno and the deep space station. In this paper，the combining method of Fast Fourier transform，Chirp Z transform and signal local reconstruction was utilized to obtain Juno’s Doppler frequency. The results show that Juno’s open loop Doppler frequency is at the level of 10 μHz，which effectively validated the method of deep space open loop measurement and provide valuable reference for China’s future deep space missions.
  • A Preliminary Discussion on the Proposal and Feasibility of Atmospheric Planet Suspension Exploration
    XING Zhuoyi, MA Yuwei, ZHU Shunjie, BAI Chongyan
    2018, 5(4): 387-391. https://doi.org/10.15982/j.issn.2095-7777.2018.04.010
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    At present, the large-scalemaneuver capability of space probes in orbiting exploration, landing exploration, exploration with rovers and sampling and return back to Earth, is greatly constrained by landform features and topography conditions. The Suspension exploration is a newly developed method for exploration mission on the planets with atmosphere. By “flight” maneuver, the probes can take full advantage of planetary atmosphere to collect more scientific exploration data. By Suspension exploration, the maneuver defects of probes can be overcame. In this paper, the concepts of a Suspension probe and its working modes are proposed. A six-degree dynamic model of the probe is set up. Together with the careful study on the environment of the planets with atmosphere in solar system, the dynamic characteristics of the Suspension probe are demonstrated and its exploration targets are listed out. Based on these study results, the evaluation coefficient of feasibility (ECoF) of the Suspension probe is proposed for the first time, thus to lay out theoretical foundation for the feasibility study on the application of Suspension probes in deep space exploration.
  • A Universal Design Method for Spacecraft On-Orbit Separation
    SHENG Ruiqing, CHEN Chunliang, XING Zhuoyi, BAI Chongyan
    2018, 5(4): 392-396. https://doi.org/10.15982/j.issn.2095-7777.2018.04.011
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    With the diversity and complexity of space exploration missions，the multi-mission and multi-target exploration with single spacecraft of multiple modules is the development trend of space technology. Under normal conditions，the separation signals trigger the continuous autonomous control，which influences the safety of spacecraft and follow-up missions. In this paper，a typical separation signal configuration and a common logical control method based on the trigger of separation signal are proposed aiming at guaranteeing the reliability of separation signal and safety of separation. A mathematical model is set up for on-orbit separation of spacecraft modules as well. Both the model and control method have been simulated，analyzed and tested with practical flight missions. The feasibility and validity of this method are demonstrated for the follow-up flight missions.