<datastore> <nextgroup><![CDATA[<a href="/module/jslib/jquery/jpage/dataproxy.jsp?page=1&appid=1&appid=1&webid=2&path='/'&columnid=1347&unitid=3691&webname='China Manned Space Engineering'&permissiontype=0"></a>]]></nextgroup> <recordset> <record><![CDATA[ <table width="705" height="110" border="0" cellspacing="0" cellpadding="8" style=" margin-bottom:10px;"> <tr> <td align="left" valign="top"><table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td height="40"> <a href='/art/2015/10/8/art_1347_22206.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Prospect of Space Life Science Study on China Space Station</a></td> </tr> </table> <table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td valign="top"><span style="line-height:22px; font-size: 15px; color:#313131">Abstract: While the China manned space program is about to enter into the space station stage, space life science in China will have its golden age. This paper reviewed the current progress in space life science worldwide.</span></td> </tr> </table></td> </tr></table><table width="100%" border="0" cellspacing="0" cellpadding="0" style=" margin-bottom:10px" height="0"> <tr> <td style="border-bottom: dotted 1px #cbcbcb;" ></td> </tr></table>]]></record> <record><![CDATA[ <table width="705" height="110" border="0" cellspacing="0" cellpadding="8" style=" margin-bottom:10px;"> <tr> <td align="left" valign="top"><table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td height="40"> <a href='/art/2015/10/8/art_1347_22207.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Fast Convergence Control on Simultaneous Approach Based Trajectory Design during Lunar Ascent</a></td> </tr> </table> <table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td valign="top"><span style="line-height:22px; font-size: 15px; color:#313131">Abstract ： In order to solve the trajectory optimization problem under complex constraints of manned spacecraft, a trajectory optimization algorithm based on simultaneous strategies was proposed in this study.</span></td> </tr> </table></td> </tr></table><table width="100%" border="0" cellspacing="0" cellpadding="0" style=" margin-bottom:10px" height="0"> <tr> <td style="border-bottom: dotted 1px #cbcbcb;" ></td> </tr></table>]]></record> <record><![CDATA[ <table width="705" height="110" border="0" cellspacing="0" cellpadding="8" style=" margin-bottom:10px;"> <tr> <td align="left" valign="top"><table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td height="40"> <a href='/art/2015/10/9/art_1347_22209.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Research on On-orbit Storage and Management Technology of Cryogenic Propellant</a></td> </tr> </table> <table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td valign="top"><span style="line-height:22px; font-size: 15px; color:#313131">Abstract: Because of the high specific impulse， nontoxic and unpolluted property， the cryogenic propellant is the first choice of the manned space flight or deep space exploration. To solve the problems of boil - off in the adverse thermal environment and the gas - liquid mixing in the microgravity， the storage and management technology of cryogenic propellant on orbit was discussed in this paper.</span></td> </tr> </table></td> </tr></table><table width="100%" border="0" cellspacing="0" cellpadding="0" style=" margin-bottom:10px" height="0"> <tr> <td style="border-bottom: dotted 1px #cbcbcb;" ></td> </tr></table>]]></record> <record><![CDATA[ <table width="705" height="110" border="0" cellspacing="0" cellpadding="8" style=" margin-bottom:10px;"> <tr> <td align="left" valign="top"><table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td height="40"> <a href='/art/2015/10/9/art_1347_22210.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Analysis of Space Docking Mechanism Buffering Test Table Based on Separation Performance</a></td> </tr> </table> <table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td valign="top"><span style="line-height:22px; font-size: 15px; color:#313131">Abstract ： To simulate the separation process in space, a buffering test table with 5 D0Fs was developed to study the rules of the relative separation speed, attitude angle and attitude angular velocity between the spacecraft and the space station.</span></td> </tr> </table></td> </tr></table><table width="100%" border="0" cellspacing="0" cellpadding="0" style=" margin-bottom:10px" height="0"> <tr> <td style="border-bottom: dotted 1px #cbcbcb;" ></td> </tr></table>]]></record> <record><![CDATA[ <table width="705" height="110" border="0" cellspacing="0" cellpadding="8" style=" margin-bottom:10px;"> <tr> <td align="left" valign="top"><table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td height="40"> <a href='/art/2015/10/9/art_1347_22211.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Simulation Study of Propulsion System Dynamics in Lunar Lander Ascend Module</a></td> </tr> </table> <table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td valign="top"><span style="line-height:22px; font-size: 15px; color:#313131">Abstract ： To simulate the lunar lander ascend module propulsion system dynamics， the models of the propulsion major parts were built. A simulation of the lunar lander ascending module propulsion classical operation was conducted.</span></td> </tr> </table></td> </tr></table><table width="100%" border="0" cellspacing="0" cellpadding="0" style=" margin-bottom:10px" height="0"> <tr> <td style="border-bottom: dotted 1px #cbcbcb;" ></td> </tr></table>]]></record> <record><![CDATA[ <table width="705" height="110" border="0" cellspacing="0" cellpadding="8" style=" margin-bottom:10px;"> <tr> <td align="left" valign="top"><table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td height="40"> <a href='/art/2015/10/9/art_1347_22212.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">POLAR Gamma Ray Burst Polarimeter onboard TG-2 Spacelab</a></td> </tr> </table> <table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td valign="top"><span style="line-height:22px; font-size: 15px; color:#313131">Abstract: It is well accepted that the measurement of the polarization level of gamma ray bursts ’ ( GRBs) prompt emission has a great potential in revealing the creation mechanism of GRBs. The space-borne Compton polarimeter POLAR developed by Chinese institutions and European institutions,</span></td> </tr> </table></td> </tr></table><table width="100%" border="0" cellspacing="0" cellpadding="0" style=" margin-bottom:10px" height="0"> <tr> <td style="border-bottom: dotted 1px #cbcbcb;" ></td> </tr></table>]]></record> <record><![CDATA[ <table width="705" height="110" border="0" cellspacing="0" cellpadding="8" style=" margin-bottom:10px;"> <tr> <td align="left" valign="top"><table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td height="40"> <a href='/art/2015/10/9/art_1347_22213.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Study on Scheme of Attitude Control Experiment Based on the First Cargo Spaceship</a></td> </tr> </table> <table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td valign="top"><span style="line-height:22px; font-size: 15px; color:#313131">Abstract ： Based on the first cargo spaceship mission and future space station requirement, the scheme of attitude control experiment system was proposed. The scheme was applied to the first cargo spaceship. On the premise of maintaining the spaceship standard platform, the expanded platform function could also be validated.</span></td> </tr> </table></td> </tr></table><table width="100%" border="0" cellspacing="0" cellpadding="0" style=" margin-bottom:10px" height="0"> <tr> <td style="border-bottom: dotted 1px #cbcbcb;" ></td> </tr></table>]]></record> <record><![CDATA[ <table width="705" height="110" border="0" cellspacing="0" cellpadding="8" style=" margin-bottom:10px;"> <tr> <td align="left" valign="top"><table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td height="40"> <a href='/art/2015/10/9/art_1347_22214.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Analysis of Rapid Orbit Determination Precision and Strategy for Tiangong-1 during Frequent Orbit Ma...</a></td> </tr> </table> <table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td valign="top"><span style="line-height:22px; font-size: 15px; color:#313131">Abstract ： The rapid space rendezvous and docking experiment of the cargo spaceship with the space station will be carried out in 2016 in China. 1t requires that the whole rendezvous and docking process be finished within six hours after the lift-off of the cargo spaceship.</span></td> </tr> </table></td> </tr></table><table width="100%" border="0" cellspacing="0" cellpadding="0" style=" margin-bottom:10px" height="0"> <tr> <td style="border-bottom: dotted 1px #cbcbcb;" ></td> </tr></table>]]></record> <record><![CDATA[ <table width="705" height="110" border="0" cellspacing="0" cellpadding="8" style=" margin-bottom:10px;"> <tr> <td align="left" valign="top"><table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td height="40"> <a href='/art/2015/10/9/art_1347_22215.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">A Method for Calibrating Empirical Density Model Based on Temperature Parameters</a></td> </tr> </table> <table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td valign="top"><span style="line-height:22px; font-size: 15px; color:#313131">Abstract ： Thermosphere atmospheric drag is a significant factor affecting most space operations of low earth spacecrafts , especially , an inherent 15% formal error of the empirical model is a barrier to improve the orbit calculation accuracy.</span></td> </tr> </table></td> </tr></table><table width="100%" border="0" cellspacing="0" cellpadding="0" style=" margin-bottom:10px" height="0"> <tr> <td style="border-bottom: dotted 1px #cbcbcb;" ></td> </tr></table>]]></record> <record><![CDATA[ <table width="705" height="110" border="0" cellspacing="0" cellpadding="8" style=" margin-bottom:10px;"> <tr> <td align="left" valign="top"><table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td height="40"> <a href='/art/2015/10/9/art_1347_22216.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Hardware Characteristic Analysis and Effects of Nonstandard Connection for 1553 B Bus</a></td> </tr> </table> <table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td valign="top"><span style="line-height:22px; font-size: 15px; color:#313131">Abstract: MIL-STD-1553B standard and related art was ripe. Even now，bus fault due to nonstandard connection was found extensively in design and test. Firstly, hardware characteristic of in and out voltage of the bus, in and out resistance and equivalent circuit was analyzed when using 1553B Bus correctly.</span></td> </tr> </table></td> </tr></table><table width="100%" border="0" cellspacing="0" cellpadding="0" style=" margin-bottom:10px" height="0"> <tr> <td style="border-bottom: dotted 1px #cbcbcb;" ></td> </tr></table>]]></record> <record><![CDATA[ <table width="705" height="110" border="0" cellspacing="0" cellpadding="8" style=" margin-bottom:10px;"> <tr> <td align="left" valign="top"><table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td height="40"> <a href='/art/2015/10/9/art_1347_22217.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">The Configuration Management Method and Engineering Practice of Tiangong-1 Spacecraft</a></td> </tr> </table> <table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td valign="top"><span style="line-height:22px; font-size: 15px; color:#313131">Abstract：The configuration management method during the Tiangong-1 development and on-orbit flight were summarized including the configuration identification , configuration change management , configuration status accounting , and configuration verification. The results show that this method can satisfy the requirements of the Tiangong-1 engineering practice.</span></td> </tr> </table></td> </tr></table><table width="100%" border="0" cellspacing="0" cellpadding="0" style=" margin-bottom:10px" height="0"> <tr> <td style="border-bottom: dotted 1px #cbcbcb;" ></td> </tr></table>]]></record> <record><![CDATA[ <table width="705" height="110" border="0" cellspacing="0" cellpadding="8" style=" margin-bottom:10px;"> <tr> <td align="left" valign="top"><table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td height="40"> <a href='/art/2015/10/9/art_1347_22218.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Numerical Simulation of Heat Transfer in Closed Two-phase Natural Circulation System Driven by Parti...</a></td> </tr> </table> <table width="100%" border="0" cellspacing="0" cellpadding="0"> <tr> <td valign="top"><span style="line-height:22px; font-size: 15px; color:#313131">Abstract： A numerical simulation model for the heat transfer in the closed two-phase natural circulation system driven by partial gravity was established. The simulations of steady operation characteristics of the two-phase loop designed for the Chinese lunar exploration spacecraft Chang’ E-3 in lunar gravity (g/6) and of a ground-based simulator in normal gravity ( 1g) showed a satisfied agreement</span></td> </tr> </table></td> </tr></table><table width="100%" border="0" cellspacing="0" cellpadding="0" style=" margin-bottom:10px" height="0"> <tr> <td style="border-bottom: dotted 1px #cbcbcb;" ></td> </tr></table>]]></record> </recordset> </datastore>