<datastore> <nextgroup><![CDATA[<a href="/module/jslib/jquery/jpage/dataproxy.jsp?page=1&appid=1&appid=1&webid=2&path='/'&columnid=1342&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/2015/9/30/art_1342_22104.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Design and Implementation of Orbit Maneuver Programming in Rendezvous and Docking Missions</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 ：Aiming at the orbit maneuver programming technique for China's rendezvous and docking mission a series of significant issues concerning the orbit rendezvous optimization emergency orbit maneuver safety orbit protection and launch window scheme were studied in this papar.</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/2015/9/30/art_1342_22105.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Research on Avoidance Strategy for Rendezvous and Docking Mission</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：Considering the characteristics of orbital motion of the target vehicle and the tracking spacecraft in the rendezvous and docking mission，three kinds of space object collision avoid¬ance strategy calculation methods were proposed according to the engineering practice， including height avoidance method， time avoidance method and combination with normal orbit control method.</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/2015/9/30/art_1342_22106.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Study on Calibration Method and Its Application in Rendezvous and Docking</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 orbit maneuver accuracy of the spacecraft can be greatly improved by calibrating the orbit maneuver effect. A method for calibrating the real velocity increment of RTN directions with precise orbit parameters was proposed in which virtual equivalent thrust was adopted to replace the impact of attitude error during the control.</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/2015/9/30/art_1342_22107.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">​Analysis and Application of Control Accuracy of Spaceship Return</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：By dividing the course of spaceship return into different stages the factors affecting the control accuracy in each stage were analyzed and the thrust-coefficient of brake engine was calibrated.</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/2015/9/30/art_1342_22108.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Study on Coordination Control Technology in Rendezvous and Docking of Two Spacecrafts</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 the manned Rendezvous and Docking( RVD) mission，Beijing Aerospace Control Center realized coordination control for the first time and the technical evolution was accomplished，including coordination system constructing，mode research，key technology breakthrough，solution design and software and hardware development.</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/2015/9/30/art_1342_22109.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Design and Implementation of Fault and Emergency Simulation System for Rendezvous and Docking Missio...</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 TT&C fault and emergency of multi-spacecrafts in rendezvous and docking missions，the evaluation environment for systematic fault simulation and integrative emergency response was developed.</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/2015/9/30/art_1342_22110.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Application of Priori Model in Orbit Return Relief of Manned 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: The pressure relief mode was adopted by manned spaceship before reentry so as to ensure the normal separation. In this paper, the impact of pressure relief on the return track was analyzed and a simplified track vent pressure empirical model was established.</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/2015/9/30/art_1342_22111.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Research on Modification of Atmospheric Density Model in Manned Space Orbit</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 error of atmospheric density model is a key factor for orbit determination and prediction in manned space flight. By analyzing the error characteristics of three models used in Chinese manned space flight missions including Jacchia，MSISE and DTM and by comparing their precision and stability，MSISE was selected as the basic model for modification.</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/2015/9/30/art_1342_22112.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Control and Accuracy Assessment of Dynamic Space Docking Test System</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 dynamic space docking test system adopts the hardware-in-the-loop (HIL) simulation method to simulate the dynamic docking processes of two spacecrafts. The simulation cycle and simulator response lag could bring low precision and instability into the test system.</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/2015/9/30/art_1342_22113.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">The Design and Implementation of Multi-mode Receiver for Rendezvous and Docking in Space</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: During the manned spaceflight mission, space to space communication system is responsible for the information exchange between two spacecrafts at the rendezvous and docking and evacuation stages.</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/2015/9/30/art_1342_22114.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Analysis on Quick Orbit Determination Ability of Relay Satellites System to User 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: According to the requirements of fast rendezvous and docking, the orbit maneuver of consumer spacecraft should be finished within two circles.</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/2015/9/30/art_1342_22115.html' target="_blank" style="line-height:20px;font-weight:bold; font-size: 15px; color:#015198;">Simulation Study on Dynamic Coupling Characteristics between the Gimbals and Magnetic Bearings of CM...</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 accuracy of gimbal-rate determines the precision of the output attitude control torque of a control moment gyroscope (CMG) . The former is determined by the torque precision of the gimbal servo motor together with the moment of inertia of the gimbals.</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>