联合国教科文组织为了持续世界各国文化的多样性和创意性,制定了"非物质文化遗产保护协约"(Convention for the Safeguarding of the Intangible Cultural Heritage)1,此次制度执行后,中韩两国因为向联合国教科文组织登载同...联合国教科文组织为了持续世界各国文化的多样性和创意性,制定了"非物质文化遗产保护协约"(Convention for the Safeguarding of the Intangible Cultural Heritage)1,此次制度执行后,中韩两国因为向联合国教科文组织登载同样的非物质文化遗产而产生了纠纷,纠纷产生的根源是因为同属汉字文化圈的两个国家具有很多相同或相似的公有文化资产。比起日本、越南等汉字文化圈国家,中韩的矛盾日益加深的原因在于从韩国移住到中国的朝鲜族的影响颇大。众所周知,中国是由56个民族所组成的多民族国家,与单一民族韩国截然不同。在政治上,朝鲜族无疑是中国的一部分,是中华人民共和国的公民,但他们的民族性却从属于韩国广义上的民族概念,因此,包括语言的口传传统及表现、公演艺术、社会仪式、节日贺宴等在内的产业方面必然会与韩国出现共同的非物质文化遗产纠纷。实行多个国家共同登载机制能够排解这种纠纷。展开更多
A circumlunar free return orbit design model that satisfies manned lunar mission constraints is established. By combining analytical method with numerical method,a serial orbit design strategy from initial value desig...A circumlunar free return orbit design model that satisfies manned lunar mission constraints is established. By combining analytical method with numerical method,a serial orbit design strategy from initial value design to precision solution is proposed. A simulation example is given,and the conclusion indicates that the method has excellent convergence performance and precision. According to a great deal of simulation results solved by the method,the free return orbit characters such as accessible moon orbit parameters,return orbit parameters,transfer delta velocity,etc. are analyzed,which can supply references to constitute manned lunar mission orbit scheme.展开更多
Point return orbit(PRO) of manned lunar mission is constrained by both lunar parking orbit and reentry corridor associated with reentry position.Besides,the fuel consumption and flight time should be economy.The patch...Point return orbit(PRO) of manned lunar mission is constrained by both lunar parking orbit and reentry corridor associated with reentry position.Besides,the fuel consumption and flight time should be economy.The patched conic equations which are adaptive to PRO are derived first,the PRO is modeled with fuel and time constraints based on the design variables of orbit parameters with clear physical meaning.After that,by combining analytical method with numerical method,a serial orbit design strategy from initial value design to precision solution is proposed.Simulation example indicates that the method has excellent convergence performance and precision.According to a great deal of simulation results by the method,the PRO characteristics such as Moon centered orbit parameters,Earth centered orbit parameters,transfer velocity change,etc.are analyzed,which can supply references to the manned lunar mission orbit scheme.展开更多
To obtain a conceptual design for a hybrid rocket motor(HRM)to be used as the Ascent Propulsion System in the Apollo lunar module,the deterministic design optimization(DDO)method is applied to the HRM design.Based on ...To obtain a conceptual design for a hybrid rocket motor(HRM)to be used as the Ascent Propulsion System in the Apollo lunar module,the deterministic design optimization(DDO)method is applied to the HRM design.Based on the results of an uncertainty analysis of HRMs,an uncertainty-based design optimization(UDO)method is also adopted to improve the design reliability.The HRM design process,which is a multidisciplinary system,is analyzed,and a mathematical model for the system design is established to compute the motor performance from the input parameters,including the input variables and model parameters.The input parameter uncertainties are quantified,and a sensitivity analysis of the model parameter uncertainties is conducted to identify the most important model parameter uncertainties for HRMs.The DDO and probabilistic UDO methods are applied to conceptual designs for an HRM to be used as a substitute for the liquid rocket motor(LRM)of the Ascent Propulsion System.The conceptual design results show that HRMs have several advantages as an alternative to the LRM of the Ascent Propulsion System,including nontoxic propellant combination,small motor volume,and comparable functions,such as restarting and throating.Comparisons of the DDO and UDO results indicate that the UDO method achieves more robust and reliable optimal designs than the DDO method.The probabilistic UDO method can be used to develop better conceptual designs for HRMs.展开更多
文摘联合国教科文组织为了持续世界各国文化的多样性和创意性,制定了"非物质文化遗产保护协约"(Convention for the Safeguarding of the Intangible Cultural Heritage)1,此次制度执行后,中韩两国因为向联合国教科文组织登载同样的非物质文化遗产而产生了纠纷,纠纷产生的根源是因为同属汉字文化圈的两个国家具有很多相同或相似的公有文化资产。比起日本、越南等汉字文化圈国家,中韩的矛盾日益加深的原因在于从韩国移住到中国的朝鲜族的影响颇大。众所周知,中国是由56个民族所组成的多民族国家,与单一民族韩国截然不同。在政治上,朝鲜族无疑是中国的一部分,是中华人民共和国的公民,但他们的民族性却从属于韩国广义上的民族概念,因此,包括语言的口传传统及表现、公演艺术、社会仪式、节日贺宴等在内的产业方面必然会与韩国出现共同的非物质文化遗产纠纷。实行多个国家共同登载机制能够排解这种纠纷。
基金supported by the National Natural Science Foundation of China (Grant No.10902121)
文摘A circumlunar free return orbit design model that satisfies manned lunar mission constraints is established. By combining analytical method with numerical method,a serial orbit design strategy from initial value design to precision solution is proposed. A simulation example is given,and the conclusion indicates that the method has excellent convergence performance and precision. According to a great deal of simulation results solved by the method,the free return orbit characters such as accessible moon orbit parameters,return orbit parameters,transfer delta velocity,etc. are analyzed,which can supply references to constitute manned lunar mission orbit scheme.
基金supported by the Open Research Foundation of Science and Technology on Aerospace Flight Dynamics Laboratory (Grant No.2012afdl005)
文摘Point return orbit(PRO) of manned lunar mission is constrained by both lunar parking orbit and reentry corridor associated with reentry position.Besides,the fuel consumption and flight time should be economy.The patched conic equations which are adaptive to PRO are derived first,the PRO is modeled with fuel and time constraints based on the design variables of orbit parameters with clear physical meaning.After that,by combining analytical method with numerical method,a serial orbit design strategy from initial value design to precision solution is proposed.Simulation example indicates that the method has excellent convergence performance and precision.According to a great deal of simulation results by the method,the PRO characteristics such as Moon centered orbit parameters,Earth centered orbit parameters,transfer velocity change,etc.are analyzed,which can supply references to the manned lunar mission orbit scheme.
基金supported by the National Natural Science Foundation of China(Grant No.51305014)the China Postdoctoral Science Foundation(Grant No.2013M540842)
文摘To obtain a conceptual design for a hybrid rocket motor(HRM)to be used as the Ascent Propulsion System in the Apollo lunar module,the deterministic design optimization(DDO)method is applied to the HRM design.Based on the results of an uncertainty analysis of HRMs,an uncertainty-based design optimization(UDO)method is also adopted to improve the design reliability.The HRM design process,which is a multidisciplinary system,is analyzed,and a mathematical model for the system design is established to compute the motor performance from the input parameters,including the input variables and model parameters.The input parameter uncertainties are quantified,and a sensitivity analysis of the model parameter uncertainties is conducted to identify the most important model parameter uncertainties for HRMs.The DDO and probabilistic UDO methods are applied to conceptual designs for an HRM to be used as a substitute for the liquid rocket motor(LRM)of the Ascent Propulsion System.The conceptual design results show that HRMs have several advantages as an alternative to the LRM of the Ascent Propulsion System,including nontoxic propellant combination,small motor volume,and comparable functions,such as restarting and throating.Comparisons of the DDO and UDO results indicate that the UDO method achieves more robust and reliable optimal designs than the DDO method.The probabilistic UDO method can be used to develop better conceptual designs for HRMs.
