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[[Image:Black Brant.jpg|thumb|right|Launch of a [[Black Brant (rocket)|Black Brant 12]] multistage [[sounding rocket]]]]
[[Image:minuteman 3 stage2.jpg|thumb|right|The second stage of a [[Minuteman&nbsp;III]] rocket]]
A '''multistage''' (or '''multi-stage''') '''rocket''' is a [[rocket]] that uses
two or more ''stages'', each of which contains its own [[Rocket engine|engines]] and [[Rocket propellant|propellant]]. A ''tandem'' or ''serial'' stage is mounted on top of another stage; a ''parallel'' stage is attached alongside another stage. The result is effectively two or more rockets stacked on top of or attached next to each other. Taken together these are sometimes called a [[launch vehicle]]. Two stage rockets are quite common, but rockets with as many as five separate stages have been successfully launched.
By jettisoning stages when they run out of propellant, the mass of the remaining rocket is decreased. This ''staging'' allows the thrust of the remaining stages to [[Newton's First Law of Motion|more easily accelerate the rocket]] to its final speed and height.
 
In serial or tandem staging schemes, the '''first stage''' is at the bottom and is usually the largest, the '''second stage''' and subsequent '''upper stages''' are above it, usually decreasing in size. In parallel staging schemes [[Solid rocket booster|solid]] or [[Liquid rocket booster|liquid]] rocket boosters are used to assist with lift-off. These are sometimes referred to as 'stage 0'. In the typical case, the first stage and booster engines fire to propel the entire rocket upwards. When the boosters run out of fuel, they are detached from the rest of the rocket (usually with some kind of small [[explosive]] charge) and fall away. The first stage then burns to completion and falls off. This leaves a smaller rocket, with the second stage on the bottom, which then fires. Known in rocketry circles as '''staging''', this process is repeated until the final stage's motor burns to completion.
 
In some cases with serial staging, the upper stage ignites ''before'' the separation- the interstage ring is designed with this in mind, and the thrust is used to help positively separate the two vehicles.
 
The [[Taurus (rocket)|Taurus rocket]] is unusual in that its 'stage 1' ignites in flight; this designation is used because its upper three stages are identical to those of the [[Pegasus (rocket)|Pegasus rocket]], with the 'stage 0' booster replacing the Pegasus' carrier aircraft.
 
==Advantages==
The main reason for multi-stage rockets and boosters is that once the fuel is exhausted, the space and structure which contained it and the motors themselves are useless and only add weight to the vehicle which slows down its future acceleration. By dropping the stages which are no longer useful, the rocket lightens itself. The thrust of future stages is able to provide more acceleration than if the earlier stage were still attached, or a single, large rocket would be capable of. When a stage drops off, the rest of the rocket is still traveling near the speed that the whole assembly reached at burn-out time. This means that it needs less total fuel to reach a given velocity and/or altitude.
 
A further advantage is that each stage can use a different type of rocket motor each tuned for its particular operating conditions. Thus the lower stage motors are designed for use at atmospheric pressure, while the upper stages can use motors suited to near vacuum conditions. Lower stages tend to require more structure than upper as they need to bear their own weight plus that of the stages above them, optimizing the structure of each stage decreases the weight of the total vehicle and provides further advantage.
 
==Disadvantages==
{{unreferenced section|date=December 2013}}
[[Image:Stages cutaway.jpg|thumb|250px|right|Cutaway drawings showing three multi-stage rockets]]
[[Image:Apollo 11 first stage separation.jpg|thumb|250px|right|Apollo 11 Saturn V first stage separation]]
[[Image:Saturn V Stages 1 and 2.jpg|thumb|250px|right|The second stage being lowered into the first stage of a [[Saturn V]] rocket]]
[[Image:Saturn V second stage.jpg|thumb|250px|right|A diagram of the second stage and how it fits into the complete rocket]]
 
On the downside, staging requires the vehicle to lift motors which are not being used until later, as well as making the entire rocket more complex and harder to build. In addition, each staging event is a significant point of failure during a launch, with the possibility of separation failure, ignition failure, and stage collision. Nevertheless the savings are so great that every rocket ever used to deliver a payload into [[orbit]] has had staging of some sort.
 
==Upper stages==
The upper stages of space launch vehicles are designed to operate at high altitude, and thus under little or no atmospheric pressure. This allows them to use lower pressure [[Rocket engine#Combustion chamber|combustion chamber]]s and still obtain near-optimum [[Rocket engine nozzle#Aerostatic back-pressure and optimum expansion|nozzle expansion ratio]]s with nozzles of reasonable size. In many low pressure [[liquid rocket]] upper stage engines, such as the Aerojet [[AJ-10]], propellants are pressure fed without need for complex turbomachinery.<ref>{{Cite web|url=http://www.astronautix.com/stages/ablestar.htm |title=Able-Star |publisher=Encyclopedia Astronautica}}</ref> Low chamber pressures also generate lower heat transfer rates, which allow ablative or radiative cooling of the combustion chambers rather than more elaborate regenerative cooling.
 
===Difference from payload===
An upper stage is a mechanism, part of the [[launch vehicle]] system, that has no other purpose than to lift upwards something else - a [[spacecraft]], [[satellite]] or another payload. The distinction is not always clear cut.  In some cases, for example, the upper stage has other uses after the payload reaches orbit, or a payload has a secondary function of providing some of the impulse required to reach orbit.  In such cases, the function of the upper stage and the payload are combined.  In some cases a payload, besides its main duties, can perform some propulsion actions on its own  (''e.g.'', moving a satellite moving from [[Geostationary transfer orbit|GTO]] to [[Geostationary orbit|GEO]]).  One case of controversial classification is the [[Polyus (spacecraft)|Polyus]] weapons platform, which required use of its on-board propulsion to reach orbit<ref name= "JBIS-2002">B. Hendrickx, "The Origins and Evolution of the Energiya Rocket Family," ''J. British Interplanetary Soc., Vol. 55,'' pp. 242-278 (2002).</ref> and, in that sense, could potentially be considered as a combination payload and upper stage.
 
===Passivation and space debris===
Upper stages of launch vehicles are a significant source of [[space debris]] from spent boosters [[:Category:Derelict satellites orbiting Earth|remaining in orbit in a non-operational state]] for many years after use, and occasionally, large debris fields created from the breakup of a single upper stage while in orbit.<ref name=loftus1989/>
 
After the 1990s, spent [[upper stage]]s are generally [[Passivation (spacecraft)|passivated]] after their use as a launch vehicle is complete in order to minimize risks while the stage [[:Category:Derelict satellites orbiting Earth|remains derelict in orbit]].<ref name=ss20111205>
{{cite web |last=Johnson|first=Nicholas |title=Space debris issues |date=2011-12-05 |url=http://www.thespaceshow.com/detail.asp?q=1666 |work=audio file, @1:03:05-1:06:20 |publisher=The Space Show |accessdate=2011-12-08 }}</ref>
 
Many early upper stages, in both the [[Soviet Union|Soviet]] and [[Federal government of the United States|U.S.]] space programs, were not passivated after mission completion.  During the initial attempts to characterize the space debris problem, it became evident that a good proportion of all [[Space debris#Boosters|debris]] was due to the breaking up of rocket upper stages, particularly [[Passivation (spacecraft)|unpassivated]] upper stage propulsion units.<ref name=loftus1989>
{{cite book |last=Loftus|first=Joseph P. |title=Orbital Debris from Upper-stage Breakup |year=1989 |publisher=AIAA |pages=227 |url=http://books.google.com/books?hl=en&lr=&id=RehH7b_kmNEC }}</ref>
 
==History and development==
From an illustration and description in the 14th century [[History of China|Chinese]] ''[[Huolongjing]]'' of [[Jiao Yu]] is the oldest known multistage rocket; this was the 'fire-dragon issuing from the water' (火龙出水, huo long chu shui), used mostly by the Chinese navy.<ref>{{Cite web|url=http://www.csonline.com.cn/zt/ztchangsha/ht/htz_2/t20031226_84913.htm|title =火龙出水(明)简介|publisher= [[星辰在线]]|date=2003-12-26|accessdate=July 17, 2008}}</ref><ref name="needham volume 5 part 7 510">Needham, Volume 5, Part 7, 510.</ref> It was a two-stage rocket that had carrier or [[booster rocket]]s that would eventually burn out, yet before they did they automatically ignited a number of smaller rocket arrows that were shot out of the front end of the missile, which was shaped like a dragon's head with an open mouth.<ref name="needham volume 5 part 7 510"/> This multi-stage rocket may be considered the ancestor to the modern [[C-602|YingJi-62]] [[Anti-ship missile|ASCM]].<ref name="needham volume 5 part 7 510"/><ref>{{Cite web|url=http://shizheng.daqi.com/editor/slide/focus_huandeng/1635618/18.html#t|title =中国YJ-62新型远程反舰导弹|publisher= [[大旗网]]|date=2007-09-30|accessdate=July 17, 2008}}</ref> The historian [[Joseph Needham]] points out that the written material and depicted illustration of this rocket come from the oldest stratum of the ''Huolongjing'', which can be dated roughly 1300-1350 AD (from the book's part 1, chapter 3, page 23).<ref name="needham volume 5 part 7 510"/>
 
Another example of an early multistaged rocket is the ''Juhwa(走火)'' of Korean development. It was proposed by [[Choe Museon]] and developed by the Firearms Bureau (火㷁道監) during the 14th century.<ref>{{Cite web|url=http://ko.wikipedia.org/wiki/%EC%A3%BC%ED%99%94_%28%EB%AC%B4%EA%B8%B0%29|title =주화 (무기)|publisher= 위키피디아|date=2008-08-30|accessdate=2013-04-18}}</ref><ref>{{Cite web|url=http://ko.wikipedia.org/wiki/%ED%99%94%ED%86%B5%EB%8F%84%EA%B0%90|title =화통도감|publisher= 위키피디아|date=2011-06-03|accessdate=2013-04-18}}</ref> The rocket had the length of 15&nbsp;cm and 13&nbsp;cm; the diameter was 2.2&nbsp;cm. It was attached to an arrow 110&nbsp;cm long; experimental records show that the first results were around 200m in range.<ref>{{Cite web|url=http://terms.naver.com/entry.nhn?cid=1608&docId=550070&mobile&categoryId=1608|title =주화 (走火)|publisher= 한국민족문화대백과|date=1999-09-25|accessdate=2013-04-18}}</ref> There are records that show Korea kept developing this technology until it came to produce the [[Singijeon]], or 'magical machine arrows' in the 16th century.
The earliest experiments with multistage rockets in Europe were made in 1551 by Austrian [[Conrad Haas]] (1509–1576), the arsenal master of the town of [[Hermannstadt]], [[Transylvania]] (now Sibiu/Hermannstadt, Romania). This concept was developed independently by at least four individuals:
*[[Kazimierz Siemienowicz]] of the [[Polish–Lithuanian Commonwealth]] (1600–1651)
*the [[Russia]]n [[Konstantin Tsiolkovsky]] (1857–1935)
*the [[United States|American]] [[Robert Goddard (scientist)|Robert Goddard]] (1882–1945)
*the [[German people|German]] [[Hermann Oberth]] (1894–1989), born in Hermannstadt, Transylvania
 
In 1947, [[Mikhail Tikhonravov]] developed a theory of parallel stages, which he called "packet rockets". In his scheme, three parallel stages were fired from lift-off, but all three engines were fueled from the outer two stages, until they are empty and could be ejected. This is more efficient than sequential staging, because the second stage engine is never just dead weight. In 1951, [[Dmitry Okhotsimsky]] carried out a pioneering engineering study of general sequential and parallel staging, with and without the pumping of fuel between stages. The design of the [[R-7 Semyorka]] emerged from that study.  The trio of rocket engines used in the first stage of the American [[Atlas I]] and [[Atlas II]] launch vehicles, arranged in a "row", used parallel staging in a similar way: the outer pair of engines existed as a jettisonable pair which would, after they shut down, drop away with the lowermost outer "skirt" structure of the booster, leaving the central "sustainer" engine to complete the first stage's engine burn towards apogee or orbit.
 
==Separation events==
Separation of each portion of a multistage rocket introduces additional [[risk]] into the success of the launch mission.  Reducing the number of separation events results in a reduction in [[complexity]].<ref>{{cite web|title=Falcon 1 - Stage Separation Reliability|url=http://www.spacex.com/falcon1.php#engine_reliability|publisher=[[SpaceX]]|accessdate=8 January 2011}}</ref>  
Separation events occur when stages or strap-on boosters separate after use, when the [[payload fairing]] separates prior to orbital insertion, or when the [[launch escape system]]—used in many early [[human spaceflight]] missions—separates after the early phase of the launch. [[Pyrotechnic fastener]]s are sometimes used to separate rocket stages.
 
==Delta-v==
With staging, the [[delta-v]] of each stage can be calculated via the [[rocket equation]] and summed:
 
<math>\Delta v = \sum_{i=0}^{n-1} {Ve}_i \cdot ln \frac {Minitial_i} {Mfinal_i} </math>
 
Where Ve is the [[effective exhaust velocity]], Minitial the initial mass, and Mfinal the mass of the rocket at the point of burnout of each stage.
 
When the Ve and mass ratios are the same for all the stages, this simplifies to:
 
<math>\Delta v = n {Ve} \cdot ln (Mratio) </math>
 
and it can be seen that the delta-v is limited only by the n, the number of stages.
 
==Alternatives to rockets==
{{Main| Spacecraft propulsion}}
 
==See also==
* [[Bumper Project]]
* [[Saturn V]]
* [[NASA]]
* [[Conrad Haas]]
* [[Reusable launch system]]
* [[Single-stage-to-orbit]]
 
==References==
{{Reflist}}
 
{{DEFAULTSORT:Multistage Rocket}}
[[Category:Aerospace engineering]]
[[Category:Chinese inventions]]
[[Category:Spacecraft propulsion]]
 
[[ja:ロケット#多段式ロケット]]

Latest revision as of 01:26, 9 January 2015

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