May 2022, Volume 4 Issue 5
    

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  • ZHU Anwen, LIU Lei, MA Shijun, Li Ming
    The history of the development of nuclear power system (nuclear power source,NPS) is reviewed in this paper,which contains radioisotope heater units (RHUs),radioisotope thermoelectric generators (RTGs),space nuclear reactors and nuclear propulsion systems. The use of NPS in deep space exploration and the current technical progress of NPS are illustrated in detail. Additionally,the problem of NPS safety is also discussed based on the international rules. The main technical issues and challenges of NPS are proposed when it’s applied in deep space exploration missions in the future.
  • ZHU Anwen, LIU Feibiao, DU Hui, MA Shijun
    In deep space exploration, due to the inability to use solar power or solar energy utilization efficiency is too low, space nuclear power is needed. So far, the isotope radioisotope decay energy is mainly used for nuclear power deep space explorers exploring the Lunar surface, Mars surface, Jupiter and beyond , while decay heat energy is used for temperature control and thermoelectric power generation. The applications of space nuclear power in deep space exploration include the Lunar base project, manned Mars flight, unmanned exploration and so on, where the fission energy is adopted. The reactors used in space fission power include reactors include liquid metal cooled reactor and gas cooled reactor. The former is able to support thermoelectric, stirling and brayton power generation, while the latter is able to support brayton and MHD power generation. The deep space explorers with the fission power attract much attention recently. From the perspective of the development of space nuclear power, the radioisotope thermoelectric generator will still play an important role in this field, and large space nuclear power combined with electric propulsion system will be an important direction of future deep space exploration.
  • XIE Jiachun, HUO Honglei, SU Zhuting, ZHAO Zehao
    NTP(Nuclear Thermal Propulsion)has special features of high specific impulse,powerful force and long operating time. NTP could be used for manned deep space exploration and large-scale cargo shipment between stars. The NTP research history and technology development in America and Russia are introduced in this paper. The trends of NTP development are summarized,namely medium thrust engine,modularized reactor core,high performance fuel element,non-nuclear experiment method and multiple function design. The key technologies of reactor design,nuclear safety protection design,fuel preparation,fuel element manufacture,exhaust handling,and engine startup,are analyzed. At last,some suggestions for NTP development in China are given,including cooperation between nuclear and aerospace industries,drawing lessons from American and Russian experiences and initiating research work as soon as possible.
  • HU Gu, ZHAO Shouzhi
    Space nuclear reactor power(SNRP)has many advantages,such as good environmental adaptability,wide power coverage,compact and small specific mass under high power conditions. SNRP has broad application prospects in military and civilian space missions,and is one of the disruptive technologies which will change the future pattern of aerospace power. In this paper,the principle,characteristics,application scopes,application prospects,development history and current situation,typical projects,application safety of SNRP are introduced. The development trends of SNRP technology are analyzed. Some insights are also given to the SNRP development in China.
  • ZHOU Jishi, LI Sha, LIU Lei, XIE Jiachun, GENG Yan
    Developing nuclear powered spacecraft is the most prospect and reliable technological approach to realize further deep space exploration. However, related development standards for integrated design of nuclear powered spacecraft have not been studied in China . Drwaing lessons from the foreign successful experience ofthe development of nuclear powered spacecraft, considering the existing standards and specifications as well as the general spacecraft design methods, the key design points were presented for developing nuclear powered spacecraft, including the Top-level Design group for engineering and Top-level Design group for spacecraft. Especially, for the utilization of space nuclear source and the safety protection, the key points and solutions for developing space nuclear source and nuclear safety design are proposed. All of these will be applied to the research and development of nuclear powered spacecraft.
  • HU Wenjun, CHEN Hongyong, CHEN Junhong, LI Shangming, HU Shaoquan, TANG yuhua
    The RHU(Radiosotope Heater Unit), RTG (Radioisotope Thermoelectric Generator) and space nuclear reactors have wide applications in deep space exploration missions. The safety principles are investigated based on their technology characteristics and the applications of nuclear sources in outer space are introduced, such as the RHU/RTG of ALRH (Apollo Lunar Radiosotope Heater), GPHS(General Purpose Heater Source) and LWRHU (Lighted Weighted Radiosotope Heater Unit), MMRTG (Multi-Mission Radioisotope Thermoelectric Generator), and space nuclear reactor of TOPAZ-II.The safety tests and analysis done by the United States and Russia are studied, and the safety validation and assess approach are reviewed, The work focuses on the technology details of the tests and analysis of RHU/RTG for different missions. The work would serve as reference for the application of nuclear source in outer space.
  • LU Liang, HU Yupeng, OUYANG Zhijiang, XIANG Yanhua, HUANG Hanjun, LI Sizhong
    To study the reliability of radioisotope heat source in the high temperature-impact composite environment, a high temperature-impact composite environment test system is developed. The main parts of this design are temperature loading system, impact test system, thermal shield system and computer information collection system. The proposed system can provide heating temperature of 500 ℃. The simulated samples of the isotope heat source were tested at 500 ℃ andhigh temperature-impact composite environmental tests are performed for 5000 times. The response temperature rise response curve and impact waveforms are obtained. The results show that this system can accomplish high temperature-impact composite environment test successfully.
  • HE Boyong, CAO Pengfei, LUO Yazhong, LI Haiyang
    An integrated design method for manned lunar mission trajectory and trans-lunar window is proposed for the manned lunar mission supported by low lunar orbit (low lunar orbit, LLO) coplanar encounter. Firstly, the basic processes and engineering constraints of the manned lunar mission supported by LLO rendezvous are analyzed. Secondly, in view of the problem of computing windows and trajectories for the tasks in different stages, a window planning strategy by iterating the power down time is proposed. Thirdly, an orbit planning model including the LLO established in the high precision model, as well as the manned and cargo trajectories established in double two-body model, is constructed. Finally, the reliability and effectiveness of the approach proposed in this paper are demonstrated by the simulation tests on the crater named after a Chinese scientists.The researching findings are useful for manned lunar orbit and window design.
  • BU Shichao, WANG Yukai, LI Wendan, LI Shuang, NIU Shengda
    In this paper, the sphere-sphere model, the ellipsoid-sphere model and the improved restrictive ellipsoid-ellipsoid model are adopted for the gravitational field modeling of the weak gravitational binary asteroid system, and the corresponding complexity and accuracy of the three models increase gradually. The elliptic integral model and the second degree second order spherical harmonic function (which has high calculation efficiency and no integrals) model are adopted to calculate the gravitational potential energy, respectively. The dynamical model of the restricted full three-body problem consisting of binary asteroid system and spacecraft is accurately described. The different gravitational field models of the binary asteroid system 1999KW4 are simulated. And the surfaces of potential energy function and zero velocity curves under different models are given respectively. The coordinate deviations of libration point under different models are compared. The results show that the ellipsoid-ellipsoid model calculated by the second degree second order spherical harmonic function has the advantages of high precision, low complexity, less calculation, higher computing speed, and can accurately model the gravitational field of the binary asteroid system.
  • LIANG Lei, SONG Xiaodong, GUO Pei, ZHENG Jiali
    Graphical user interface(GUI)is crucial for astronaut’s on-orbit operation in manned spacecraft. Given that the massive and mutable technical requirements of the human-computer interaction, and the long development period and severe technical difficulties , the design methods based on MiniGUI control are categorized and analyzed firstly. After that, based on above information, a customized design method is presented, which can add configurable attributes for users. Finally, the results of practical applications demonstrate that the display effect is enhanced dramatically and the design efficiency is improved considerably.
  • CHEN Lue, PING Jinsong, ZHANG Jianhui, LIU Qing, YUE Shilei, CHEN Yongqiang, WANG Jizhou, LI Wenxiao