Ballute

2025-10-11T21:20:28Z

92.29.148.178: /* Design */

{{short description|Parachute-like braking device}}
{{Distinguish|balut (disambiguation){{!}}balut}}
[[File:F-111F dropping high-drag bombs.jpg|thumb|upright=1.5|Ballute-equipped [[Mark 82 bomb]]s, Mk-82AIRs, being dropped by an American [[F-111]] attack aircraft]]
A '''ballute''' (a [[portmanteau]] of ''[[balloon]]'' and ''[[parachute]]'') is a parachute-like braking device optimized for use at high altitudes and [[supersonic]] velocities.

The original ballute configuration was invented in 1958<ref>{{cite web |title=Balloon (Balloon-Parachute) |url=https://stratocat.com.ar/stratopedia/125.htm |website=Stratocat |publisher=Stratopedia |access-date=22 August 2023}}</ref> by the [[Goodyear Tire and Rubber Company|Goodyear]] company. The innovation soon caught the attention of other organisations, including [[NASA]]; the agency incorporated ballutes into the escape system of the [[Project Gemini|Gemini]] spacecraft. It has subsequently seen extensive use within the aerospace sector as a means of retarding the descent of various payloads, such as sections of [[rocket]]s and atmospheric probes. Various proposals involving ballutes, such as for deorbiting/recovering low-mass [[satellite]]s and interplanetary research programmes, have been issued in recent decades.

==Design==
The ballute is an inflatable device used to generate drag.<ref name="JPL2000" /> In terms of its basic configuration, it is a cone-shaped balloon, featuring a [[toroid]]al burble fence (an inflated structure intended to ensure [[flow separation]]) that is fitted around its widest point.<ref name="nasa 1969">{{cite web |last1=Mayhue |first1=Robert J. |last2=Eckstrom |first2=Clinton V. |date=May 1969 |title=Flight-test results from Supersonic deployment of an 18-foot-diameter (5.49 meter) ballute decelerator |url=https://ntrs.nasa.gov/api/citations/19690017080/downloads/19690017080.pdf |publisher=ntrs.nasa.gov}}</ref> The burble fence acts to stabilize the ballute as it decelerates through different flow regimes, typically descending from faster (even supersonic) flows into subsonic speeds.<ref name="nasa 1969" /><ref>{{cite web |url = https://www.newhaven.edu/_resources/documents/academics/surf/past-projects/2014/anthony-mastromarino-paper.pdf |title = Aerodynamic Study of a Ballute Using Computational Fluid Dynamics |publisher = newhaven.edu |first1= Anthony R. |last1=Mastromarino III |first2=Maria-Isabel |last2=Carnasciali |date = 2014}}</ref> The design of the ballute, particularly its drop-like shaping, make it more suitable for decelerating at extreme speeds than a conventional parachute.<ref name="wiredballute">{{cite web |url = https://www.wired.com/2014/01/bastard-named-ballute/ |title = A Bastard Named Ballute |publisher = wired.com |first = Kristian |last = von Bengtson |date = 30 January 2014}}</ref>[[File:20110430 BurbleFence 000.svg|thumb|Sketch of ballute components]]Ballutes can be categorised into three primary configurations, these being cocoon ballutes that enclose their payloads, attached ballutes that attach directly to the base of their payloads, and towed ballutes that trail after their payloads.<ref name = "JPL2000"/> The isotensoid ballute has been recognised as the standard configuration, although other arrangements have been tested. It has been proposed that ballutes could be arranged in both stacked toroidal and tension cone form factors.<ref name=ss2011/> Some ballute configurations are specialised to certain purposes or industries, such as the aerospace sector.<ref>{{cite book |chapter-url = https://link.springer.com/chapter/10.1007/978-3-8348-9911-8_4 |chapter = Ballute Spacecraft Configuration options |first = Hannes |last = Griebel |title = Reaching High Altitudes on Mars with an Inflatable Hypersonic Drag Balloon (Ballute) |publisher = Vieweg+Teubner |date = 2011|pages = 33–43 |doi = 10.1007/978-3-8348-9911-8_4 |isbn = 978-3-8348-1425-8 }}</ref><ref>{{cite web |url = http://images.spaceref.com/fiso/2016/062916_Bandeau_Clark/Bandeau-Clark_6-29-16.pdf |title = Large Supersonic Ballutes: Testing and Applications |publisher = [[Jet Propulsion Laboratory]] |author = Ian Clark and Erich Brandeau |date = 29 June 2019}}</ref>

By attaching a ballute to an air-dropped object, such as a [[bomb]] or an aerospace payload, it should (provided it is of sufficient size and has correctly deployed) limit its rate of descent, potentially minimising damage to the payload on contact with the ground.<ref name = "nasa 1969"/><ref>{{cite web |url = https://copenhagensuborbitals.com/the-cutting-edge-of-supersonic-ballute-manufacturing/ |title = The Cutting Edge of Supersonic Ballute Manufacturing |date = 12 December 2019 |publisher = [[Copenhagen Suborbitals]] |accessdate = 28 June 2020}}</ref> They can generate a relatively high amount of drag for their mass, making them attractive in weight-constrained scenarios typical to aerospace applications.<ref name = "JPL2000"/>

Inflation of a ballute is typically achieved either by a gas generator or by external air being forced into the structure by an arrangement of ram air inlets.<ref name = "nasa 1969"/> The design of the inflation mechanism is particularly critical to its successful application; if the inlets are too small or too few, the ballute will not maintain its shape and collapse, while excessive inlet flow likely results in overpressure and raising the risk of bursting.<ref name = "wiredballute"/> Accordingly, the ballute has to be precisely designed to conform with the environmental conditions it is to be exposed to; similarly, the deployment ought to be with similar care, such as in respect to timing. Improper deployment is likely to cause failure, as excessive deceleration forces risk snapping fixing points and tearing fabric; tangling is another potential risk.<ref name = "wiredballute"/><ref>{{cite web |url = https://copenhagensuborbitals.com/droptesting-an-improved-ballute-design/ |title = Droptesting an Improved Ballute Design |date = 11 September 2019 |publisher = [[Copenhagen Suborbitals]] |accessdate = 28 June 2020}}</ref>

==Applications==
The ballute was originally developed in response to the instability of early supersonic parachutes, proving to be an attractive alternative.<ref name = "JPL2000"/>

The ballute has been used on freefall [[gravity bomb|bombs]] dropped from an aircraft, helping to both retard and stabilise the descent.<ref name = "JPL2000"/>

The ballute has been extensively used through the aerospace industry.<ref name = "nasa 1969"/> One of its earliest uses in the sector was as an element of the astronaut's [[Launch escape system|launch escape]] equipment aboard [[NASA]]'s [[Project Gemini|Gemini]] spacecraft;<ref>{{cite web |url = http://www.hq.nasa.gov/office/pao/History/SP-4203/ch8-4.htm |title = A Set of Breakthroughs |publisher = hq.nasa.gov |accessdate = 28 June 2020}}</ref> it was also being used to slow down the descent of the [[Arcas (rocket)|Arcas]], an early American [[Sounding rocket|rocketsondes]], by the mid-1960s.<ref>{{cite web |url = https://apps.dtic.mil/dtic/tr/fulltext/u2/625785.pdf |archive-url = https://web.archive.org/web/20200629234714/https://apps.dtic.mil/dtic/tr/fulltext/u2/625785.pdf |url-status = dead |archive-date = June 29, 2020 |title = Development of Ballute for Retardation of Arcas rocketsondes |author = J.J. Graham, Jr. |publisher = Air Force Cambridge Research Laboratories |date = December 1965}}</ref> During the 1960s, the agency performed detailed research into the ballute as an aerodynamic decelerator system on other planets, such as [[Mars]].<ref name = "nasa 1969"/>

In the 1984 film ''[[2010: The Year We Make Contact]]'', a ballute is used on the ''Leonov'' spacecraft to shield it from the effects of heating during [[aerobraking]], allowing the ''Leonov'' to slow itself without expending fuel and establish an orbit around Jupiter's moon [[Io (moon)|Io]].<ref>{{cite web|title=Movie: 2010. The Year We Make Contact (1984), Roy Scheider: Dr. Heywood Floyd|website=[[IMDb]] |url=https://www.imdb.com/title/tt0086837/characters/nm0001702|quote=We don't have enough fuel to slow ourselves down, so we are about to use a technique called aerobraking. The theory is, we will enter the outer layer of Jupiter's atmosphere using what is called a "ballute" for a shield. The atmosphere will slow us down, and Jupiter's gravity will grab hold of us and slingshot us around behind the dark side.|access-date=December 31, 2022}}</ref>
[[File:4-ldsd sfdt1 recovery-0218.jpg|thumb|Recovery of a trailing ballute tested as a part of NASA's [[Low-Density Supersonic Decelerator|Low-density Supersonic Decelerator]] program]]
In 2000, NASA's [[Jet Propulsion Laboratory]] was researching the ballute, emphasising its potential for use in both [[aerocapture]] and [[aerobraking]] operations.<ref name = "JPL2000">{{cite web |url = https://www2.jpl.nasa.gov/adv_tech/ballutes/Blut_ppr/jlh-4iaa.pdf |title = A Review of Ballute Technology for Planetary Aerocapture |first = Jeffery L. |last = Hall |publisher = [[Jet Propulsion Laboratory]] |date = 2 May 2000}}</ref><ref>{{cite web |url = https://www.space.com/6602-ballutes-studied-hypersonic-space-vehicles.html |title = Ballutes Studied For Hypersonic Space Vehicles |publisher = space.com |first = Bill |last = Christensen |date = 21 April 2009}}</ref> Around that same period, the [[European Space Agency]] was also evaluating the use of inflatable shielding as a means of facilitating the controlled reentry of spacecraft.<ref>{{cite web |url = http://www.esa.int/esapub/bulletin/bullet103/marraffa103.pdf |title = Inflatable Re-Entry Technologies: Flight Demonstration and Future Prospect |publisher = [[European Space Agency]] |first1= L. |last1=Marraffa|first2=D. |last2=Kassing|first3=P|last3=Baglioni|first4=D. |last4=Wilde|first5=S. |last5=Walther|first6=K. |last6=Pitchkhadze |first7=V. |last7=Finchenko |date = August 2000}}</ref>

Various proposed interplanetary atmospheric probes have incorporated ballutes; for envisioned missions to [[Venus]], they shall act not only to control atmospheric entry but to provide buoyant support for the sensor payload as well.<ref name = "JPL2000"/><ref>{{cite web |url = https://engineering.purdue.edu/people/james.m.longuski.1/ConferencePapersPresentations/2005ADual-UseBalluteforEntryandDescentDuringPlanetaryMissions.pdf |title = A Dual-use Ballute for entry and descent during planetary missions |publisher = engineering.purdue.edu |first1 = Kristin L. (Gates) |last1=Medlock |first2=James M. |last2=Longuski |first3=Daniel T. |last3=Lyons |date = 2005}}</ref> Landers on [[Mars]] may also use ballutes during direct atmospheric entry, while cocoon-style ballutes may also be adopted for orbital transfer vehicles in orbit around [[Earth]]. Particularly large ballutes may be used for planetary aerocapture purposes on various planetary bodies around the [[Solar System]].<ref name = "JPL2000"/> Furthermore, extended designs using inflatable tension cone ballute technology have been proposed for deorbiting [[Nanosatellite|NanoSats]] and recovering low-mass (< {{cvt|1.5|kg|disp=or}}) [[satellite]]s from [[low Earth orbit]].<ref name="ss2011">{{cite web |url=http://digitalcommons.usu.edu/smallsat/2011/all2011/68/ |title=NanoSat Deorbit and Recovery System (DRS) to Enable New Missions |date= 2011 |publisher=Small Sat 2011 |work=conference paper |accessdate=22 January 2012}}</ref><ref>{{cite web |url = https://www.researchgate.net/publication/3869014 |title = Attached inflatable ballute for spacecraft deceleration |publisher = IEE Xplore |volume = 7 |date = February 2000}}</ref>

In early 2012, [[Armadillo Aerospace]] used a ballute during the testing of its STIG-A rocket.<ref name=aa2012>{{cite web |title=Armadillo Launches a STIG-A Rocket - Captures Awesome Image of Ballute |url=http://www.universetoday.com/93281/armadillo-launches-a-stig-a-rocket-captures-awesome-image-of-ballute/ |accessdate=17 July 2012}}</ref><ref name="as20111224">{{cite web |title=Reentry System—CubeSat Recovery System |url=http://www.andrews-space.com/content-main.php?mainsection=Mjc2 |year=2008 |publisher=Andrews Space |accessdate=24 December 2011 |url-status=dead |archiveurl=https://web.archive.org/web/20120101193223/http://www.andrews-space.com/content-main.php?mainsection=Mjc2 |archivedate=1 January 2012 }}</ref> In February 2015, the Danish nonprofit aerospace organisation [[Copenhagen Suborbitals]] were engaged in testing a ballute for its Nexø rockets.<ref>{{cite web|title= Warp speed, mr. Zulu! |url=http://ing.dk/blog/warp-speed-mr-zulu-173845# |date=25 February 2015 |publisher=[[Ingeniøren]] |accessdate=22 April 2018 |language= da}}</ref> In April 2018, [[Elon Musk]] tweeted that [[SpaceX]] would recover [[Falcon 9]] second stages with the help of a "giant party balloon",<ref>{{cite web |url = https://twitter.com/elonmusk/status/985655249745592320 |title = SpaceX will try to bring rocket upper stage back from orbital velocity using a giant party balloon |author = Elon Musk |author-link = Elon Musk |publisher = [[Twitter]] |date = 16 April 2018}}</ref> after the company [[SpaceX reusable launch system development program|started landing the rocket's first stages routinely]]. However, the plan was called off. In August 2019, [[Peter Beck]], founder and CEO of [[Rocket Lab]], announced that they would attempt to recover their Electron rocket's lower stage utilising a ballute for supersonic deceleration, enabling the stage to be captured in mid-air by a helicopter.<ref>{{Cite web |url=https://everydayastronaut.com/rocket-lab-electron-reuse/ |title=Can Rocket Lab really catch a rocket with a helicopter?! |date=10 August 2019 |website=Everyday Astronaut |language=en-US |access-date=15 October 2019}}</ref>

==See also==
* [[Index of aviation articles]]

==References==
{{Reflist}}

==External links==
* [http://www.parachutehistory.com/other/ballute.html Ballute on parachutehistory.com]
* [https://scitechdaily.com/tag/ballute/ Ballute news on scitechdaily.com]

[[Category:Drogues]]
[[Category:Spacecraft components]]
[[Category:Aircraft components]]
[[Category:Spaceflight technology]]

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