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<span id="openzim-page-title" class="mw-page-title-main"><span class="mw-page-title-main">Universal Rocket Module</span></span>
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</style><table class="infobox hproduct"><caption class="infobox-title fn">URM-1</caption><tbody><tr><th scope="row" class="infobox-label">Manufacturer</th><td class="infobox-data brand"><a href="Khrunichev_State_Research_and_Production_Space_Center" title="Khrunichev State Research and Production Space Center">Khrunichev</a></td></tr><tr><th scope="row" class="infobox-label">Country of origin</th><td class="infobox-data">Russia</td></tr><tr><th scope="row" class="infobox-label">Used on</th><td class="infobox-data"><a href="Angara_(rocket_family)" title="Angara (rocket family)">Angara</a> stage 1 and boosters</td></tr><tr><th colspan="2" class="infobox-header">General characteristics</th></tr><tr><th scope="row" class="infobox-label">Height</th><td class="infobox-data">25.7 m (84 ft)</td></tr><tr><th scope="row" class="infobox-label">Diameter</th><td class="infobox-data">2.9 m (9 ft 6 in)</td></tr><tr><th scope="row" class="infobox-label">Gross mass</th><td class="infobox-data">142,400 kg (313,900 lb)</td></tr><tr><th scope="row" class="infobox-label">Propellant mass</th><td class="infobox-data">132,600 kg (292,300 lb)
</td></tr><tr><th colspan="2" class="infobox-header" style="background: #ddf;">URM-1</th></tr><tr><th scope="row" class="infobox-label">Powered by</th><td class="infobox-data">1 <a href="RD-191" title="RD-191">RD-191</a></td></tr><tr><th scope="row" class="infobox-label">Maximum thrust</th><td class="infobox-data">1,920 kN (430,000 lb<sub>f</sub>) (sea level)</td></tr><tr><th scope="row" class="infobox-label"><a href="Specific_impulse" title="Specific impulse">Specific impulse</a></th><td class="infobox-data">311 seconds (3.05 km/s) (sea level)</td></tr><tr><th scope="row" class="infobox-label">Burn time</th><td class="infobox-data"><b>Angara 1.2</b>: 214 s<br><b>Angara A5 Booster</b>: 214 s<br><b>Angara A5 Core</b>: 325 s</td></tr><tr><th scope="row" class="infobox-label">Propellant</th><td class="infobox-data"><a href="Liquid_oxygen" title="Liquid oxygen">LOX</a>/<a href="Kerosene" title="Kerosene">Kerosene</a></td></tr><tr style="display:none"><td colspan="2">
</td></tr></tbody></table>
<table class="infobox hproduct"><caption class="infobox-title fn">URM-2</caption><tbody><tr><th scope="row" class="infobox-label">Manufacturer</th><td class="infobox-data brand"><a href="Khrunichev_State_Research_and_Production_Space_Center" title="Khrunichev State Research and Production Space Center">Khrunichev</a></td></tr><tr><th scope="row" class="infobox-label">Country of origin</th><td class="infobox-data">Russia</td></tr><tr><th scope="row" class="infobox-label">Used on</th><td class="infobox-data"><a href="Angara_(rocket_family)" title="Angara (rocket family)">Angara A5</a> stage 2</td></tr><tr><th colspan="2" class="infobox-header">General characteristics</th></tr><tr><th scope="row" class="infobox-label">Height</th><td class="infobox-data">6.9 m (23 ft)</td></tr><tr><th scope="row" class="infobox-label">Diameter</th><td class="infobox-data">3.6 m (12 ft)</td></tr><tr><th scope="row" class="infobox-label">Propellant mass</th><td class="infobox-data">36,000 kg (79,000 lb)
</td></tr><tr><th colspan="2" class="infobox-header" style="background: #ddf;">URM-2</th></tr><tr><th scope="row" class="infobox-label">Powered by</th><td class="infobox-data">1 <a href="RD-0124" title="RD-0124">RD-0124A</a></td></tr><tr><th scope="row" class="infobox-label">Maximum thrust</th><td class="infobox-data">294 kN (66,000 lb<sub>f</sub>)</td></tr><tr><th scope="row" class="infobox-label"><a href="Specific_impulse" title="Specific impulse">Specific impulse</a></th><td class="infobox-data">359 seconds (3.52 km/s)</td></tr><tr><th scope="row" class="infobox-label">Burn time</th><td class="infobox-data">424 s</td></tr><tr><th scope="row" class="infobox-label">Propellant</th><td class="infobox-data"><a href="Liquid_oxygen" title="Liquid oxygen">LOX</a>/<a href="Kerosene" title="Kerosene">Kerosene</a></td></tr><tr style="display:none"><td colspan="2">
</td></tr></tbody></table>
<p><b>Universal Rocket Module</b> (<b>URM</b>) is the name of the modular <a href="Liquid_rocket" class="mw-redirect" title="Liquid rocket">liquid fuelled</a> first and second stage of the <a href="Angara_(rocket_family)" title="Angara (rocket family)">Angara</a> <a href="Expendable_launch_system" title="Expendable launch system">expendable launch system</a>. The first stage and booster variant is referred to as <b>URM-1</b>, while the second stage is referred to as <b>URM-2</b>. The URM-2 is derived from the <a href="Soyuz-2_(rocket)" class="mw-redirect" title="Soyuz-2 (rocket)">Soyuz-2</a> Block I second stage.<sup id="cite_ref-:0_1-0" class="reference"><a href="#cite_note-:0-1"><span class="cite-bracket">[</span>1<span class="cite-bracket">]</span></a></sup>
</p><p>URM-1 is a unitary structure 2.9 meters in diameter and 25 meters in length that includes an oxidizer tank, a fuel tank (both tanks being coupled by a spacer) and an <a href="RD-191" title="RD-191">RD-191</a> engine burning <a href="RP-1" title="RP-1">RP-1</a> fuel with <a href="Liquid_oxygen" title="Liquid oxygen">liquid oxygen</a> producing a thrust of 1.92 <a href="Newton_(unit)" title="Newton (unit)">MN</a>.<sup id="cite_ref-2" class="reference"><a href="#cite_note-2"><span class="cite-bracket">[</span>2<span class="cite-bracket">]</span></a></sup> URM-1 was first flown in 2014 on the <a href="Angara-1.2pp" title="Angara-1.2pp">Angara 1.2PP</a> suborbital test flight. Angara can fly with either one URM-1 in the case of <a href="Angara_1.2" class="mw-redirect" title="Angara 1.2">Angara 1.2</a> and Angara 1.2PP, or one URM-1 as a sustainer core with four additional URM-1s as boosters for <a href="Angara_A5" title="Angara A5">Angara A5</a>.<sup id="cite_ref-:0_1-1" class="reference"><a href="#cite_note-:0-1"><span class="cite-bracket">[</span>1<span class="cite-bracket">]</span></a></sup>
</p><p>URM-2 is a modified Block I stage, 3.6 meters in diameter and 6.9 meters in length. It is powered by a single RD-0124A producing 294 kilonewtons, derived from Block I's <a href="RD-0124" title="RD-0124">RD-0124</a>. URM-2 was first flight tested on Angara 1.2PP, but will fly in operation only on the <a href="Angara_A5" title="Angara A5">Angara A5</a>. The operational <a href="Angara_1.2" class="mw-redirect" title="Angara 1.2">Angara 1.2</a> will also use a modified Block I powered by the RD-0124A as a second stage, though this stage will have a diameter of no more than 2.9 meters.<sup id="cite_ref-3" class="reference"><a href="#cite_note-3"><span class="cite-bracket">[</span>3<span class="cite-bracket">]</span></a></sup>
</p><p>The <a href="Naro-1" title="Naro-1">Naro-1</a> <a href="Launch_vehicle" title="Launch vehicle">launch vehicle</a> was based on the URM-1 with a reduced thrust <a href="RD-191" title="RD-191">RD-191</a>, called RD-151, combined with a solid-fueled second stage built by
<a href="South_Korea" title="South Korea">Republic of Korea</a> <a href="Korea_Aerospace_Research_Institute" title="Korea Aerospace Research Institute">KARI</a>.
</p>
<div class="mw-heading mw-heading2"><h2 id="See_also">See also</h2></div>
<ul><li><a href="Universal_Rocket" title="Universal Rocket">Universal Rocket </a></li>
<li><a href="Angara_(rocket_family)" title="Angara (rocket family)">Angara rocket family</a></li>
<li><a href="Liquid_rocket_booster" title="Liquid rocket booster">Liquid rocket booster</a></li>
<li><a href="Common_Core_Booster" title="Common Core Booster">Common Core Booster</a>, similar concept for <a href="Atlas_V" title="Atlas V">Atlas V</a></li>
<li><a href="Common_Booster_Core" title="Common Booster Core">Common Booster Core</a>, similar concept for <a href="Delta_IV" title="Delta IV">Delta IV</a></li></ul>
<div class="mw-heading mw-heading2"><h2 id="External_links">External links</h2></div>
<ul><li><a rel="nofollow" class="external text" href="https://web.archive.org/web/20170219072240/http://www.khrunichev.ru/main.php?id=44">Angara page by Khrunichev Space Center <i>(Archived, Russian)</i></a></li>
<li><a rel="nofollow" class="external text" href="http://www.russianspaceweb.com/angara.html">Angara page on RussianSpaceWeb</a></li></ul>
<div class="mw-heading mw-heading2"><h2 id="Notes">Notes</h2></div>
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</style><cite class="citation web cs1"><a rel="nofollow" class="external text" href="http://www.spaceflight101.com/angara-a5.html">"Angara A5"</a>. <i>Spaceflight 101</i><span class="reference-accessdate">. Retrieved <span class="nowrap">July 14,</span> 2014</span>.</cite></span>
</li>
<li id="cite_note-2"><span class="mw-cite-backlink"><b><a href="#cite_ref-2">^</a></b></span> <span class="reference-text"><cite class="citation web cs1 cs1-prop-script cs1-prop-foreign-lang-source"><a rel="nofollow" class="external text" href="https://web.archive.org/web/20170219072240/http://www.khrunichev.ru/main.php?id=44"><bdi lang="ru">ГКНПЦ имени М.В.Хруничева | Семейство ракет-носителей "Ангара"</bdi></a> [Angara Launch Vehicle family] (in Russian). Archived from <a rel="nofollow" class="external text" href="http://www.khrunichev.ru/main.php?id=44">the original</a> on 19 February 2017.</cite></span>
</li>
<li id="cite_note-3"><span class="mw-cite-backlink"><b><a href="#cite_ref-3">^</a></b></span> <span class="reference-text"><cite id="CITEREFZak" class="citation web cs1">Zak, Anatoly. <a rel="nofollow" class="external text" href="http://www.russianspaceweb.com/angara1.html">"Angara-1"</a>. <i>RussianSpaceWeb</i><span class="reference-accessdate">. Retrieved <span class="nowrap">July 12,</span> 2014</span>.</cite></span>
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