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	<id>https://arolstar52-zhtest.hf.space/index.php?action=history&amp;feed=atom&amp;title=CE-20</id>
	<title>CE-20 - 版本历史</title>
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	<updated>2026-07-16T21:11:05Z</updated>
	<subtitle>在这个wiki上该页的修订历史</subtitle>
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	<entry>
		<id>https://arolstar52-zhtest.hf.space/index.php?title=CE-20&amp;diff=2079293&amp;oldid=prev</id>
		<title>imported&gt;Evesiesta：​摘掉{{Link Style}}：共1个跨语言链接</title>
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		<updated>2022-12-24T10:22:36Z</updated>

		<summary type="html">&lt;p&gt;&lt;a href=&quot;/wiki/MediaWiki:Gadget-fixlinkstyle.js&quot; title=&quot;MediaWiki:Gadget-fixlinkstyle.js&quot;&gt;摘掉&lt;/a&gt;{{Link Style}}：共1个跨语言链接&lt;/p&gt;
&lt;p&gt;&lt;b&gt;新页面&lt;/b&gt;&lt;/p&gt;&lt;div&gt;{{多個問題|&lt;br /&gt;
{{expand|time=2016-11-05T10:28:35+00:00}}&lt;br /&gt;
{{update|time=2016-11-05T10:28:35+00:00}}&lt;br /&gt;
}}&lt;br /&gt;
{{infobox rocket engine&lt;br /&gt;
  |image= CE-20 Engine Config Model.png&lt;br /&gt;
  |image_size=250&lt;br /&gt;
  |caption=Model of CE-20&lt;br /&gt;
  |name=CE-20&lt;br /&gt;
  |country_of_origin={{IND}}&lt;br /&gt;
  |designer=[[印度太空研究組織]]&lt;br /&gt;
  |manufacturer={{link-en|液體推進系統中心|Liquid Propulsion Systems Centre}}&lt;br /&gt;
  |日期=2015&lt;br /&gt;
  |purpose= [[上升段助推器]]&lt;br /&gt;
  |predecessor=&lt;br /&gt;
  |status=Under Development&lt;br /&gt;
&lt;br /&gt;
  |cycle=[[燃氣發生器循環]]&lt;br /&gt;
  |type=液態&lt;br /&gt;
  |fuel=[[液氢]]&lt;br /&gt;
  |oxidiser=[[液氧]]&lt;br /&gt;
  |capacity=&lt;br /&gt;
  |combustion_chamber=1&lt;br /&gt;
  |nozzle_ratio=100&lt;br /&gt;
&lt;br /&gt;
  |thrust(SL)=&lt;br /&gt;
  |thrust(Vac)=196.5 kN&lt;br /&gt;
  |specific_impulse_vacuum={{convert|434|isp}}&lt;br /&gt;
  |specific_impulse_sea_level=&lt;br /&gt;
  |chamber_pressure=60.00 bar&lt;br /&gt;
  |thrust_to_weight=&lt;br /&gt;
  |diameter=&lt;br /&gt;
  |length=&lt;br /&gt;
  |dry_weight=588 kg&lt;br /&gt;
  |references      =&amp;lt;ref&amp;gt;{{Cite web |url= https://www.isro.gov.in/launchers/high-thrust-cryogenic-engine-ce20-development |title= High Thrust Cryogenic Engine (CE20) Development |publisher= ISRO |language= en |access-date= 2022-02-16 |archive-date= 2022-02-16 |archive-url= https://web.archive.org/web/20220216034754/https://www.isro.gov.in/launchers/high-thrust-cryogenic-engine-ce20-development }}&amp;lt;/ref&amp;gt;&lt;br /&gt;
}}&lt;br /&gt;
&lt;br /&gt;
&lt;br /&gt;
&amp;#039;&amp;#039;&amp;#039;CE-20&amp;#039;&amp;#039;&amp;#039;是一種[[印度]]為了给[[地球同步衛星運載火箭3型號|GSLV-III]]提供上升段動力而發展的低溫[[火箭發動機|火箭引擎]]，由液體推進系統中心（[[印度太空研究組織]]的附屬機構）開發。它是印度第一個使用[[燃氣發生器循環]]的低溫火箭引擎。&lt;br /&gt;
&lt;br /&gt;
==参考资料==&lt;br /&gt;
{{reflist}}&lt;br /&gt;
&lt;br /&gt;
&lt;br /&gt;
&lt;br /&gt;
&lt;br /&gt;
&lt;br /&gt;
[[Category:火箭发动机]]&lt;br /&gt;
[[Category:印度航天]]&lt;br /&gt;
[[Category:航天器推进]]&lt;br /&gt;
[[Category:航空航天工程]]&lt;br /&gt;
&lt;br /&gt;
{{Rocket Engines}}&lt;/div&gt;</summary>
		<author><name>imported&gt;Evesiesta</name></author>
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