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RD-0110
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Please contact <a href="mailto:(Anatoly Zak) agzak@russianspaceweb.com">Anatoly Zak</a>.</p> <hr> <p align="center"> </p> <div align="left"><div align="left"><div align="left"><div align="left"></div> </div> </div> </div> </td> <td height=210 align="left" valign="top" bordercolor="#CCCCCC" bgcolor="#FFFFFF" ><p align="center" class="mainHeadline">The RD-0110 engine <br> for the third stage of the Soyuz rocket</p> <p align="center" class="mainHeadline"><img src="images/rockets/engines/rd0110/rd0110_1.jpg" alt="RD-0110" width="640" height="480"></p> <p align="center" class="picCaption">The RD-0110 engine which powers the third stage of Soyuz rockets.</p> <p align="left"><font size="1" face="Verdana, Arial, Helvetica, sans-serif"><a class="addthis_button" href="http://www.addthis.com/bookmark.php?v=250&pub=xa-4a9567347f52c441"><img src="http://s7.addthis.com/static/btn/v2/lg-share-en.gif" width="125" height="16" alt="Bookmark and Share" style="border:0"/></a> <script type="text/javascript" src="http://s7.addthis.com/js/250/addthis_widget.js?pub=xa-4a9567347f52c441"></script> </font></p> <p align="center"><font size="1" face="Verdana, Arial, Helvetica, sans-serif"> <script type="text/javascript"><!-- google_ad_client = "pub-7664737336508994"; //468x60, created 1/5/08 google_ad_slot = "4972932600"; google_ad_width = 468; google_ad_height = 60; //--></script> <script type="text/javascript" src="http://pagead2.googlesyndication.com/pagead/show_ads.js"></script> </font></p> <p class="bodyText">Intended for the third stage of several rockets in the <a href="soyuz.html">Soyuz family</a>, including Soyuz-U and Soyuz-FG, the RD-0110 (11D55) engine descended from the RD-0107 engine, which was used on the Voskhod launcher. That engine, in turn, derived from RD-0106, which powered the second stage of the <a href="r9.html">R-9</a> ICBM. Like most previous engines on upper stages in the Soyuz family, RD-0110 was developed at KB Khimavtomatiki design bureau, a.k.a KBKhA, in the city of Voronezh. Ya. I. Gershkovich led the design team. (<a href="sources.html#shustov">145</a>) The engine is mass produced at the Voronezh Mechanical Plant, VMZ.</p> <p class="bodyText">Equipped with four main combustion chambers, the RD-0110 engine uses a single turbopump, feeding all chambers. The engine was designed to work in conjunction with four steering nozzles with the thrust of 6 kH. While the main chambers are fixed to the frame of the engine, steering nozzles can swivel along a single axis, providing pitch, yaw and course control for the rocket, in addition to giving some extra thrust. (<a href="sources.html#rachuk">331</a>)</p> <p align="center"><img src="images/rockets/engines/rd0110/combustion_chamber_1.jpg" alt="chamber" width="730" height="426"></p> <p align="center" class="picCaption">A combustion chamber of the RD-0110 engine during production at Voronezh Mechanical Plant in 2016.</p> <hr> <p align="center"><img src="images/rockets/engines/rd0110/vernier_1.jpg" alt="vernier" width="730" height="442"></p> <p align="center" class="picCaption">Vernier nozzle of the RD-0110 engine during production at the Voronezh Mechanical Plant in 2016.</p> <hr> <p align="left"> </p> <p align="left"><font size="1" face="Verdana, Arial, Helvetica, sans-serif"><a class="addthis_button" href="http://www.addthis.com/bookmark.php?v=250&pub=xa-4a9567347f52c441"><img src="http://s7.addthis.com/static/btn/v2/lg-share-en.gif" width="125" height="16" alt="Bookmark and Share" style="border:0"/></a> <script type="text/javascript" src="http://s7.addthis.com/js/250/addthis_widget.js?pub=xa-4a9567347f52c441"></script> </font></p> <p align="center"><font size="1" face="Verdana, Arial, Helvetica, sans-serif"> <script type="text/javascript"><!-- google_ad_client = "pub-7664737336508994"; //468x60, created 1/5/08 google_ad_slot = "4972932600"; google_ad_width = 468; google_ad_height = 60; //--></script> <script type="text/javascript" src="http://pagead2.googlesyndication.com/pagead/show_ads.js"></script> </font></p> <p> </p> <p class="tableHeadline"><font color="#000000">Specifications for the RD-0110 engine:</font></p> <table width="100%" border="0" cellspacing="0" cellpadding="3"> <tr> <td bgcolor="#CCCCCC" class="tableText">Fuel</td> <td bgcolor="#CCCCCC" class="tableText"><div align="right">Kerosene</div></td> </tr> <tr> <td bgcolor="#FFFFFF" class="tableText">Oxidizer</td> <td bgcolor="#FFFFFF" class="tableText"><div align="right">Liquid oxygen</div></td> </tr> <tr> <td bgcolor="#CCCCCC" class="tableText">Thrust</td> <td bgcolor="#CCCCCC" class="tableText"><div align="right">298 kH (30.4 tons) (<a href="sources.html#shustov">145</a>)</div></td> </tr> <tr> <td bgcolor="#FFFFFF" class="tableText">Specific impulse</td> <td bgcolor="#FFFFFF" class="tableText"><div align="right">3,195 meters per second (<a href="sources.html#shustov">145</a>)</div></td> </tr> <tr> <td bgcolor="#CCCCCC" class="tableText">Burn time</td> <td bgcolor="#CCCCCC" class="tableText"><div align="right">230 or 240 seconds (<a href="sources.html#shustov">145</a>)</div></td> </tr> <tr> <td class="tableText">Mass of the engine</td> <td class="tableText"><div align="right">408.5 - 410 kilograms (<a href="sources.html#shustov">145</a>)</div></td> </tr> <tr> <td bgcolor="#CCCCCC" class="tableText">Height of the engine</td> <td bgcolor="#CCCCCC" class="tableText"><div align="right">1,575 millimeters (<a href="sources.html#shustov">145</a>)</div></td> </tr> <tr> <td class="tableText">Diameter of the engine</td> <td class="tableText"><div align="right">2,240 millimeters (<a href="sources.html#shustov">145</a>)</div></td> </tr> <tr> <td bgcolor="#CCCCCC" class="tableText">Combustion chamber pressure</td> <td bgcolor="#CCCCCC" class="tableText"><div align="right">7 MPa (69 atmospheres)</div></td> </tr> </table> <p align="center"> </p> <p align="center" class="footerCredit">Page author: Anatoly Zak; Last update: <!-- #BeginDate format:Am1 -->November 11, 2020<!-- #EndDate --> </p> <p align="center" class="footerCredit">All rights reserved</p> <p align="center" class="footerCredit"> </p></td> <td width="200" align="left" valign="top" bordercolor="#CCCCCC" bgcolor="#CCCCCC" ><p><a href="insider-content.html"><img src="images/logos/insider_content_200.jpg" alt="insider content" width="200" height="486" border="0"></a></p> <p> </p> <p><font size="1" face="Verdana, Arial, Helvetica, sans-serif"><a href="javascript:;"><img src="images/spacecraft/manned/soyuz/soyuz_lv_stage3_2.jpg" alt="soyuz" width="200" height="150" border="0" onClick="MM_openBrWindow('images/rockets/soyuz/stage3/stage3_s1_1.jpg','stage','scrollbars=yes,resizable=yes,width=500,height=385')"></a></font></p> <p class="picCaptionSidebar">A third stage of the Soyuz rocket. Copyright © 2001 Anatoly Zak</p> <hr> <p align="center" class="picCaptionSidebar"><img src="images/rd0110_2.jpg" alt="RD-0110" width="150" height="200"></p> <p class="picCaptionSidebar">The four-chamber RD-0110 engine, which was used for several decades on the third stage of the Soyuz family of launchers became the focus of upgrades needed to build the Soyuz-2 launcher. Copyright © 2001 Anatoly Zak</p> <hr> <p align="center" class="picCaptionSidebar"><img src="images/rockets/soyuz/rd0110_0124_2.jpg" alt="RD-0110" width="200" height="87"></p> <p align="left" class="picCaptionSidebar">Comparison of the RD-0110 engine installed on the <a href="soyuz_lv.html">Soyuz rocket</a> (left) and the RD-0124 engine designed for Soyuz-2. <a href="javascript:;" onClick="MM_openBrWindow('images/rockets/soyuz/rd0110_0124_1.jpg','Soyuz','scrollbars=yes,resizable=yes,width=640,height=287')">Click to enlarge</a>. 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