| 词条 | RD-0216 |
| 释义 |
|name =RD-0216 (РД-0216) |image = |image_size = |caption = |country_of_origin=USSR |date = |first_date = 1965-04-19[1] |last_date = |designer =OKB-154[1] |manufacturer =PO Motorostroitel or Perm[3] |purpose =ICBM propulsion |associated =UR-100[1] |predecessor = |successor =RD-0235 |status =Retired |type =liquid |oxidiser =N2O4 |fuel =UDMH |mixture_ratio = |cycle =Oxidizer Rich Staged combustion[1] |pumps = |description = |combustion_chamber=1 |nozzle_ratio = |thrust ={{convert|219|kN|lbf}} |thrust_at_altitude= |thrust(Vac) = |thrust(SL) = |throttle_range = |thrust_to_weight= |chamber_pressure={{convert|17.4|MPa|psi}} |specific_impulse={{convert|313|isp|abbr=on}} |specific_impulse_vacuum= |specific_impulse_sea_level= |total_impulse = |burn_time = |restarts = |gimbal = |capacity = |dimensions = |length = |diameter = |dry_weight = |used_in =UR-100 Core Stage [12] |references = |notes = }}{{Infobox rocket engine |name =RD-0235 (РД-0235) |image = |image_size = |caption = |country_of_origin=USSR |date = |first_date = 1973-04-09[13] |last_date = |designer =OKB-154[13] |manufacturer =Krasny Oktyabr factory[3] |purpose =ICBM propulsion |associated =UR-100N, Rokot and Strela[13] |predecessor = |successor = |status =Out of Production |type =liquid |oxidiser =N2O4[17] |fuel =UDMH[17] |mixture_ratio = |cycle =Oxidizer Rich Staged combustion[13] |pumps = |description = |combustion_chamber=1[17] |nozzle_ratio = |thrust ={{convert|240|kN|lbf}}[17] |thrust_at_altitude= |thrust(Vac) = |thrust(SL) = |throttle_range = |thrust_to_weight= |chamber_pressure={{convert|17.5|MPa|psi}}[17] |specific_impulse={{convert|320|isp|abbr=on}}[17] |specific_impulse_vacuum= |specific_impulse_sea_level= |total_impulse = |burn_time = |restarts = |gimbal = |capacity = |dimensions = |length = |diameter = |dry_weight = |used_in =UR-100N Second Stage [17] |references = |notes = }} The RD-0216 and RD-0217 are liquid rocket engines, burning N2O4 and UDMH in the oxidizer rich staged combustion cycle.[1] The only difference between the RD-0216 and the RD-0217 is that the latter has a heat exchanger to heat the pressuring gasses for the tanks. Three RD-0216 and one RD-0217 were used on the first stage of the UR-100 ICBM.[28] The engines were manufactured until 1974 and stayed in operational use until 1991. More than 1100 engines were produced. For the UR-100N project, while first stage propulsion was based on the more powerful RD-0233 engine. The second stage used a variation of the RD-0217 called the RD-0235 (GRAU Index 15D113).[30] It used a vacuum optimized nozzle extension, and thus had an extra 10s of isp and {{convert|21|kN|lbf}}[17] of more thrust. It has a fixed nozzle and relies on the RD-0236 vernier engine for thrust vectoring. While the engine has been out of production for a while, the UR-100NU and the Rokot and Strela use it as of 2015.[17] See also{{Portal | Space}}
References1. ^1 {{cite web |url=http://www.astronautix.com/engines/rd0217.htm |title=RD-0217 |website=Encyclopedia Astronautica |accessdate=2015-06-19 |deadurl=yes |archiveurl=https://web.archive.org/web/20171111000000/http://www.astronautix.com/engines/rd0217.htm |archivedate=2017-11-11 |df= }} [1][2][3][4][5][6][7]2. ^1 2 3 4 5 6 7 8 9 {{cite web |url=http://www.astronautix.com/engines/rd0235.htm |title=RD-0235 |website=Encyclopedia Astronautica |accessdate=2015-06-19 |deadurl=yes |archiveurl=https://web.archive.org/web/20150824113758/http://www.astronautix.com/engines/rd0235.htm |archivedate=2015-08-24 |df= }} 3. ^1 2 3 4 5 {{cite web |url=http://www.kbkha.ru/?p=8&cat=10&prod=50 |title= RD-0216, RD-0217. Intercontinental ballistic missile RS-10 |publisher=KBKhA |accessdate=2015-06-19}} 4. ^1 2 3 4 {{cite web |url=http://www.kbkha.ru/?p=8&cat=10&prod=47 |title= RD-0216, RD-0217. Intercontinental ballistic missile RS-10 |publisher=KBKhA |accessdate=2015-06-19}} 5. ^1 {{cite web |url=http://www.khrunichev.ru/main.php?id=43 |title= Rockot Launch Vehicle |publisher=Khrunichev State Research and Production Space Center |accessdate=2015-06-19}} 6. ^1 2 {{cite journal |title=Liquid Propellant Engines in the Soviet Union |last=Lardier |first=Christian |journal=Thirty-third IAA History Symposium |volume=19 |pages=39–73 |publisher=American Astronautical Society |}} 7. ^1 {{cite web |url=http://www.russianspaceweb.com/ur100.html |title=UR-100 Family |last=Zak |first=Anatoly |website=RussianSpaceWeb.com |accessdate=2015-06-19}} }} External links
4 : Rocket engines of the Soviet Union|Rocket engines using hypergolic propellant|Rocket engines using the staged combustion cycle|KBKhA rocket engines |
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