Wikipedia

AJ10: Difference between revisions

Browse history interactively
← Previous edit
Content deleted Content added
VisualWikitext
Cleanup infobox
 
(6 intermediate revisions by 5 users not shown)
Line 1:
{{short description|Hypergolic rocket engine manufactured by Aerojet}}
{{Distinguish|RL10}}
{{Infobox rocket engine
| country_of_origin = United States = {{USA}}
| image = Delta II second stage.jpg
| caption = AJ10-118K▼
|image_size=300
| name = AJ10
▲|caption=AJ10-118K
| date = 1957–present▼
|name=AJ10
| manufacturer = [[Aerojet]], [[Aerojet Rocketdyne]]▼
▲|date = 1957–present
| purpose = [[Upper stage]]
▲|manufacturer = [[Aerojet]], [[Aerojet Rocketdyne]]
| status = In use
|purpose = [[Upper stage]]/[[spacecraft]] propulsion
| cycle = [[Pressure-fed engine (rocket)|Pressure-fed engine]]▼
|status=In use
| combustion_chamber = 1▼
▲|cycle=[[Pressure-fed engine (rocket)|Pressure-fed engine]]
| thrust(Vac) = {{cvt|43.7 |kN}}▼
▲|combustion_chamber=1
| specific_impulse_vacuum = {{convert|270-319|isp}}
▲|thrust(Vac)=43.7 kN
|specific_impulse_vacuum chamber_pressure =from {{convert|2707-9|ispbar}} on AJ10-101<ref>{{cite webencyclopedia |url=http://www.astronautix.com/aengines/aj10-101aj10118.htmlhtm |title=AJ10-101118 |encyclopedia=Encyclopedia Astronautica |access-date=2008-06-22 25|url-status=dead October|archive-url=https://web.archive.org/web/20080706190928/http://astronautix.com/engines/aj10118.htm |archive-date=2008-07-06 2022}}</ref> to {{convert|319|isp}} on AJ10-118K
| thrust_to_weight = ▼
<ref>{{cite web |url=http://www.b14643.de/Spacerockets_2/United_States_5/Delta_II/Design/DeltaII_1.htm |title=Delta II Design |access-date= 6 June 2012 | publisher=Gunter's Space Page}}</ref>
| diameter = {{cvt|0.84|m}}
|chamber_pressure={{convert|7-9|bar}}<ref>{{cite encyclopedia |url=http://www.astronautix.com/engines/aj10118.htm |title=AJ10-118 |encyclopedia=Encyclopedia Astronautica |access-date=2008-06-22 |url-status=dead |archive-url=https://web.archive.org/web/20080706190928/http://astronautix.com/engines/aj10118.htm |archive-date=2008-07-06 }}</ref>
| length =
▲|thrust_to_weight=
| dry_weight = {{cvt|90–100|kg}}
|diameter=0.84 m
| type = liquid
|length=
| fuel = [[Aerozine 50]]▼
|dry_weight=90–100 kg
| oxidizer = {{chem2|N2O4|link=Dinitrogen tetroxide}}
|predecessor (optional)
| used_in = {{plainlist|▼
|successor
|type = liquid
▲|fuel = [[Aerozine 50]]
|oxidizer = [[Dinitrogen tetroxide|{{chem|N|2|O|4}}]]
▲|used_in = {{plainlist|
*[[Vanguard (rocket)|Vanguard]] ([[Able (rocket stage)|Delta-A]])
*[[Thor-Able|Thor]]/[[Atlas-Able|Atlas]] ([[Able (rocket stage)|Able]])
*[[Thor-Delta]]/[[Delta (rocket family)|Delta A-N, Super-Six]] (Stage 2)
*[[Thor-Ablestar]] ([[Ablestar]])
*Delta [[Delta 0100|0100]]/[[Delta 1000|1000]]/[[Delta 2000|2000]]/[[Delta 3000|3000]] ([[Delta-F (rocket stage)|Delta-F]])
Line 35 ⟶ 32:
*[[Apollo program|Apollo]] ([[Apollo service module|service module]])
*[[Space Shuttle]] ([[Space Shuttle Orbital Maneuvering System|Orbital Maneuvering System]])
*[[Orion (spacecraft)|Orion]] ([[OrionEuropean serviceService moduleModule|service module]])}}
}}
The '''AJ10''' is a [[hypergolic]] [[rocket engine]] manufactured by [[Aerojet Rocketdyne]] (previously [[Aerojet]]). It has been used to propel the upper stages of several [[launch vehicle]]s, including the [[Delta II]] and [[Titan III]]. Variants were and are used as the service propulsion engine for the [[Apollo command and service module]], in the [[Space Shuttle]] [[Space Shuttle Orbital Maneuvering System|Orbital Maneuvering System]], and on the [[European Service Module]] – part of [[NASA]]'s [[Orion (spacecraft)|Orion spacecraft]].
 
==Variants==
 
It was first used in the [[Able (rocket stage)|Delta-A/Able]] second stage of the [[Vanguard rocket]], in the '''AJ10-11837''' configuration. It was initially fueled by [[nitric acid]] and [[UDMH]].<ref name="EA-118">{{cite web |url=http://www.astronautix.com/engines/aj10118.htm |title=AJ10-118 |last=Wade| first=Mark |publisher=Encyclopedia Astronautica |access-date=2008-06-22 |archive-url=https://web.archive.org/web/20080706190928/http://astronautix.com/engines/aj10118.htm |archive-date=6 July 2008 |url-status=dead }}</ref> An AJ10 engine was first fired in flight during the third Vanguard launch, on 17 March 1958, which successfully placed the [[Vanguard 1]] satellite into orbit.
 
The '''AJ10-101''' engine was used on an uprated version of the Able stage, used on [[Atlas-Able]] and [[Thor-Able]] rockets. The first AJ10-101 flight, with a Thor-Able, occurred on 23 April 1958; however, the Thor failed before the upper Able stage fired. The second flight, which saw the first in flight firing of an AJ10-101 engine, occurred on 10 July 1958.<ref>{{cite web |url=http://www.astronautix.com/lvs/thorable.htm |archive-url=https://web.archive.org/web/20020228155848/http://www.astronautix.com/lvs/thorable.htm |url-status=dead |archive-date=February 28, 2002 |title=Thor-Able |last=Wade |first=Mark |publisher=Encyclopedia Astronautica |access-date=2008-05-24}}</ref>
Line 55 ⟶ 52:
 
The '''AJ10-190''' engine was used on the [[Space Shuttle]] [[Space Shuttle Orbital Maneuvering System|Orbital Maneuvering System]] (OMS) for orbital insertion, on-orbit maneuvers, and de-orbiting, first flown in 1981. They produced {{Convert|26.7|kN}} of thrust with a [[specific impulse]] (''I''<sub>sp</sub>) of 316&nbsp;seconds.<ref name="OME">{{Cite web |url=http://www.astronautix.com/engines/ome.htm |title=OME|access-date=4 January 2010|publisher=Encyclopedia Astronautica|year=2009|author=Encyclopedia Astronautica |url-status=dead |archive-url=https://web.archive.org/web/20100113042044/http://astronautix.com/engines/ome.htm|archive-date=13 January 2010|df=dmy-all}}</ref>
Following the retirement of the Shuttle, these engines waswere repurposed for use on the [[Orion (spacecraft)|Orion]] spacecraft's [[OrionEuropean serviceService moduleModule|service module]].<ref>{{cite web |url=http://www.nasaspaceflight.com/2015/06/plum-brook-orion-service-module-testing/ |title=Plum Brook prepped for EM-1 Orion Service Module testing |last=Bergin |first=Chris |work=NASASpaceFlight.com |date=20 June 2015 |access-date=28 July 2015}}</ref> This variant uses [[Monomethylhydrazine]] as fuel, with nitrogen tetroxide (N<sub>2</sub>O<sub>4</sub>) as oxidizer.<ref>{{Cite web |url=https://www.rocket.com/sites/default/files/documents/In-Space%20Data%20Sheets%209.13.19.pdf |title=Aerojet Rocketdyne - In-Space Propulsion Data Sheets |access-date=2019-12-07 |archive-date=2020-01-11 |archive-url=https://web.archive.org/web/20200111232719/https://www.rocket.com/sites/default/files/documents/In-Space%20Data%20Sheets%209.13.19.pdf |url-status=dead }}</ref>
 
The '''AJ10-118K''' engine was used on the [[Delta II]] rocket's upper stage, [[Delta-K]]. It used Aerozine 50 as fuel and nitrogen tetroxide (N<sub>2</sub>O<sub>4</sub>) as oxidizer.<ref>{{cite web |title=Delta II Stage 2 Engine |url=http://www.rocket.com/delta-ii-stage-2-engine |publisher=[[Aerojet Rocketdyne]] |access-date=22 January 2017 |archive-url=https://web.archive.org/web/20170314070920/http://www.rocket.com/delta-ii-stage-2-engine |archive-date=14 March 2017 |url-status=dead }}</ref> The AJ10-118K engine variant was used from 1989 and retired at the conclusion of the [[ICESat-2]] launch on 15 September 2018.
Retrieved from "https://en.wikipedia.org/wiki/AJ10"