Solid-propellant rocket - Revision history

imported>Biosaurt: The Chinese rockets satisfy the definition of a solid propellant rocket. Using the word "primitive" multiple times in a paragraph is unnecessary and redundant.

2025-12-13T02:14:40Z

The Chinese rockets satisfy the definition of a solid propellant rocket. Using the word "primitive" multiple times in a paragraph is unnecessary and redundant.

← Previous revision		Revision as of 02:14, 13 December 2025
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	[[File:RIAN archive 303890 A battery of Katyusha during the 1941-1945 Great Patriotic War.jpg\|thumb\|A battery of [[Katyusha rocket launcher]]s fires at German forces during the [[Battle of Stalingrad]], 6 October 1942]]		[[File:RIAN archive 303890 A battery of Katyusha during the 1941-1945 Great Patriotic War.jpg\|thumb\|A battery of [[Katyusha rocket launcher]]s fires at German forces during the [[Battle of Stalingrad]], 6 October 1942]]
	[[File:Aerojet260.png\|thumb\|Aerojet 260 motor test, 25 September 1965]]		[[File:Aerojet260.png\|thumb\|Aerojet 260 motor test, 25 September 1965]]
	The medieval [[Song dynasty]] Chinese invented ~~a very primitive form of~~ solid-propellant rocket.<ref>{{Cite book \|title=Space Science in China \|last= Hu \|first=Wen-Rui \|year=1997 \|isbn= 978-9056990237 \|publication-date=August 20, 1997 \|page=15\|publisher= CRC Press }}</ref> Illustrations and descriptions in the 14th century Chinese military treatise ''[[Huolongjing]]'' by the Ming dynasty military writer and philosopher [[Jiao Yu]] confirm that the Chinese in 1232 used ~~proto~~ solid propellant rockets then known as "[[fire arrows]]" to drive back the Mongols during the [[Siege of Kaifeng (1232)]].<ref name="Greatrix 2012 1">{{Cite book \|title=Powered Flight: The Engineering of Aerospace Propulsion \|last=Greatrix \|first= David R. \|publisher=Springer \|year=2012 \|isbn=978-1447124849 \|pages=1}}</ref><ref name="Nielsen 1997 2–4">{{Cite book \|title=Blast Off!: Rocketry for Elementary and Middle School Students P \|last= Nielsen \|first= Leona \|publisher= Libraries Unlimited \|year=1997 \|isbn= 978-1563084386 \|pages=2–4}}</ref> Each arrow took ~~a primitive~~ form of a simple, solid-propellant rocket tube that was filled with gunpowder. One open end allowed the gas to escape and was attached to a long stick that acted as a guidance system for flight direction control.<ref name="Nielsen 1997 2–4"/><ref name="Greatrix 2012 1"/>		The medieval [[Song dynasty]] Chinese invented the solid-propellant rocket.<ref>{{Cite book \|title=Space Science in China \|last= Hu \|first=Wen-Rui \|year=1997 \|isbn= 978-9056990237 \|publication-date=August 20, 1997 \|page=15\|publisher= CRC Press }}</ref> Illustrations and descriptions in the 14th century Chinese military treatise ''[[Huolongjing]]'' by the Ming dynasty military writer and philosopher [[Jiao Yu]] confirm that the Chinese in 1232 used solid propellant rockets then known as "[[fire arrows]]" to drive back the Mongols during the [[Siege of Kaifeng (1232)]].<ref name="Greatrix 2012 1">{{Cite book \|title=Powered Flight: The Engineering of Aerospace Propulsion \|last=Greatrix \|first= David R. \|publisher=Springer \|year=2012 \|isbn=978-1447124849 \|pages=1}}</ref><ref name="Nielsen 1997 2–4">{{Cite book \|title=Blast Off!: Rocketry for Elementary and Middle School Students P \|last= Nielsen \|first= Leona \|publisher= Libraries Unlimited \|year=1997 \|isbn= 978-1563084386 \|pages=2–4}}</ref> Each arrow took the form of a simple, solid-propellant rocket tube that was filled with gunpowder. One open end allowed the gas to escape and was attached to a long stick that acted as a guidance system for flight direction control.<ref name="Nielsen 1997 2–4"/><ref name="Greatrix 2012 1"/>

	The first rockets with tubes of cast iron were used by the [[Kingdom of Mysore]] under [[Hyder Ali]] and [[Tipu Sultan]] in the 1750s. These rockets had a reach of targets up to a mile and a half away. These were extremely effective in the [[Second Anglo-Mysore War]] that ended in a humiliating defeat for the [[British East India Company]]. Word of the success of the Mysore rockets against the British triggered research in England, France, Ireland and elsewhere. When the British finally conquered the fort of [[Siege of Seringapatam (1799)\|Srirangapatana]] in 1799, hundreds of rockets were shipped off to the [[Royal Arsenal]] near London to be reverse-engineered. This led to the first industrial manufacture of military rockets with the [[Congreve rocket]] in 1804.<ref name="Bowdoin 2004">{{Cite book \|title=Rockets and Missiles: The Life Story of a Technology\|last= Van Riper \|first= Bowdoin \|publisher= The Johns Hopkins University Press \|year=2004 \|isbn= 978-0801887925 \|pages=14–15}}</ref>		The first rockets with tubes of cast iron were used by the [[Kingdom of Mysore]] under [[Hyder Ali]] and [[Tipu Sultan]] in the 1750s. These rockets had a reach of targets up to a mile and a half away. These were extremely effective in the [[Second Anglo-Mysore War]] that ended in a humiliating defeat for the [[British East India Company]]. Word of the success of the Mysore rockets against the British triggered research in England, France, Ireland and elsewhere. When the British finally conquered the fort of [[Siege of Seringapatam (1799)\|Srirangapatana]] in 1799, hundreds of rockets were shipped off to the [[Royal Arsenal]] near London to be reverse-engineered. This led to the first industrial manufacture of military rockets with the [[Congreve rocket]] in 1804.<ref name="Bowdoin 2004">{{Cite book \|title=Rockets and Missiles: The Life Story of a Technology\|last= Van Riper \|first= Bowdoin \|publisher= The Johns Hopkins University Press \|year=2004 \|isbn= 978-0801887925 \|pages=14–15}}</ref>

imported>Arjayay: Duplicate word removed

2025-10-04T12:32:31Z

Duplicate word removed

← Previous revision		Revision as of 12:32, 4 October 2025
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	===Zinc–sulfur (ZS) propellants===		===Zinc–sulfur (ZS) propellants===
	Composed of powdered [[zinc]] metal and powdered sulfur (oxidizer), ZS or "micrograin" is another pressed propellant that does not find any practical application outside specialized amateur rocketry circles due to its poor performance (as most ZS burns outside the combustion chamber) and fast linear burn rates on the order of 2 m/s. ZS is most often employed as a novelty propellant as the rocket accelerates extremely quickly leaving a spectacular large orange fireball behind it.		Composed of powdered [[zinc]] metal and powdered sulfur (oxidizer), ZS or "micrograin" is another pressed propellant that does not find any practical application outside specialized amateur rocketry circles due to its poor performance (as most ZS burns outside the combustion chamber) and fast linear burn rates on the order of 2 m/s. ZS is most often employed as a novelty propellant as the rocket accelerates extremely quickly leaving a spectacular large orange fireball behind it.

	~~==="Candy" propellants===~~
	In general, [[rocket candy]] propellants are an oxidizer (typically potassium nitrate) and a sugar fuel (typically [[dextrose]], [[sorbitol]], or [[sucrose]]) that are cast into shape by gently melting the propellant constituents together and pouring or packing the [[amorphous]] [[colloid]] into a mold. Candy propellants generate a low-medium specific impulse of roughly {{convert\|130\|isp\|abbr=on}} and, thus, are used primarily by amateur and experimental rocketeers.

	===Double-base (DB) propellants===		===Double-base (DB) propellants===
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	A powdered oxidizer and powdered metal fuel are intimately mixed and immobilized with a rubbery binder (that also acts as a fuel). Composite propellants are often either [[ammonium nitrate\|ammonium-nitrate]]-based (ANCP) or [[ammonium perchlorate\|ammonium-perchlorate]]-based (APCP). Ammonium nitrate composite propellant often uses [[magnesium]] and/or [[aluminium]] as fuel and delivers medium performance (I<sub>sp</sub> of about {{convert\|210\|isp\|abbr=on}}) whereas [[ammonium perchlorate composite propellant]] often uses aluminium fuel and delivers high performance: vacuum I<sub>sp</sub> up to {{convert\|296\|isp\|abbr=on}} with a single-piece nozzle or {{convert\|304\|isp\|abbr=on}} with a high-area-ratio telescoping nozzle.<ref name="spaceandtech.com"/> Aluminium is used as fuel because it has a reasonable specific energy density, a high volumetric energy density, and is difficult to ignite accidentally. Composite propellants are cast, and retain their shape after the rubber binder, such as [[Hydroxyl-terminated polybutadiene]] (HTPB), [[cross-links]] (solidifies) with the aid of a curative additive. Because of its high performance, moderate ease of manufacturing, and moderate cost, APCP finds widespread use in space, military, and amateur rockets, whereas cheaper and less efficient ANCP finds use in amateur rocketry and [[gas generator]]s. [[Ammonium dinitramide]], NH<sub>4</sub>N(NO<sub>2</sub>)<sub>2</sub>, is being considered as a 1-to-1 chlorine-free substitute for ammonium perchlorate in composite propellants. Unlike ammonium nitrate, ADN can be substituted for AP without a loss in motor performance.		A powdered oxidizer and powdered metal fuel are intimately mixed and immobilized with a rubbery binder (that also acts as a fuel). Composite propellants are often either [[ammonium nitrate\|ammonium-nitrate]]-based (ANCP) or [[ammonium perchlorate\|ammonium-perchlorate]]-based (APCP). Ammonium nitrate composite propellant often uses [[magnesium]] and/or [[aluminium]] as fuel and delivers medium performance (I<sub>sp</sub> of about {{convert\|210\|isp\|abbr=on}}) whereas [[ammonium perchlorate composite propellant]] often uses aluminium fuel and delivers high performance: vacuum I<sub>sp</sub> up to {{convert\|296\|isp\|abbr=on}} with a single-piece nozzle or {{convert\|304\|isp\|abbr=on}} with a high-area-ratio telescoping nozzle.<ref name="spaceandtech.com"/> Aluminium is used as fuel because it has a reasonable specific energy density, a high volumetric energy density, and is difficult to ignite accidentally. Composite propellants are cast, and retain their shape after the rubber binder, such as [[Hydroxyl-terminated polybutadiene]] (HTPB), [[cross-links]] (solidifies) with the aid of a curative additive. Because of its high performance, moderate ease of manufacturing, and moderate cost, APCP finds widespread use in space, military, and amateur rockets, whereas cheaper and less efficient ANCP finds use in amateur rocketry and [[gas generator]]s. [[Ammonium dinitramide]], NH<sub>4</sub>N(NO<sub>2</sub>)<sub>2</sub>, is being considered as a 1-to-1 chlorine-free substitute for ammonium perchlorate in composite propellants. Unlike ammonium nitrate, ADN can be substituted for AP without a loss in motor performance.

	Polyurethane-bound aluminium-APCP solid fuel was used in the submarine-launched [[Polaris missile]]s.<ref>{{Cite web\|url=https://fas.org/nuke/guide/usa/slbm/a-1.htm\|title = Polaris A1 - United States Nuclear Forces}}</ref> APCP used in the [[Space Shuttle Solid Rocket Boosters\|space shuttle Solid Rocket Boosters]] consisted of ammonium perchlorate (oxidizer, 69.6% by weight), aluminium (fuel, 16%), iron oxide (a catalyst, 0.4%), polybutadiene [[acrylonitrile]] (PBAN) polymer (a non-urethane rubber binder that held the mixture together and acted as secondary fuel, 12.04%), and an epoxy [[Curing (chemistry)\|curing]] agent (1.96%).<ref name="sts-newsref-srb">{{cite web \| url = http://science.ksc.nasa.gov/shuttle/technology/sts-newsref/srb.html \| title = Shuttle Solid Rocket Boosters \| publisher = NASA \| access-date = 2015-10-02 \| archive-date = 2019-04-30 \| archive-url = https://web.archive.org/web/20190430095734/https://science.ksc.nasa.gov/shuttle/technology/sts-newsref/srb.html \| url-status = dead }}</ref><ref name="returntoflight-system-SRB">{{cite web \| url = http://www.nasa.gov/returntoflight/system/system_SRB.html \| title = Solid Rocket Boosters \| publisher = NASA \| access-date = 2015-10-02 \| archive-date = 2013-04-06 \| archive-url = https://web.archive.org/web/20130406193019/http://www.nasa.gov/returntoflight/system/system_SRB.html \| url-status = dead }}</ref> It developed a specific impulse of 242 seconds (2.37 km/s) at sea level or 268 seconds (2.63 km/s) in a vacuum. The ~~2005-2009~~ [[Constellation Program]] was to use a similar PBAN-bound APCP.<ref>{{cite news \|title=NASA Tests Engine With an Uncertain Future \|url=https://www.nytimes.com/2010/08/31/science/space/31rocket.html?hpw \|work=[[New York Times]] \|date=August 30, 2010 \|access-date=2010-08-31 \| first=Kenneth \| last=Chang}}</ref>		Polyurethane-bound aluminium-APCP solid fuel was used in the submarine-launched [[Polaris missile]]s.<ref>{{Cite web\|url=https://fas.org/nuke/guide/usa/slbm/a-1.htm\|title = Polaris A1 - United States Nuclear Forces}}</ref> APCP used in the [[Space Shuttle Solid Rocket Boosters\|space shuttle Solid Rocket Boosters]] consisted of ammonium perchlorate (oxidizer, 69.6% by weight), aluminium (fuel, 16%), iron oxide (a catalyst, 0.4%), polybutadiene [[acrylonitrile]] (PBAN) polymer (a non-urethane rubber binder that held the mixture together and acted as secondary fuel, 12.04%), and an epoxy [[Curing (chemistry)\|curing]] agent (1.96%).<ref name="sts-newsref-srb">{{cite web \| url = http://science.ksc.nasa.gov/shuttle/technology/sts-newsref/srb.html \| title = Shuttle Solid Rocket Boosters \| publisher = NASA \| access-date = 2015-10-02 \| archive-date = 2019-04-30 \| archive-url = https://web.archive.org/web/20190430095734/https://science.ksc.nasa.gov/shuttle/technology/sts-newsref/srb.html \| url-status = dead }}</ref><ref name="returntoflight-system-SRB">{{cite web \| url = http://www.nasa.gov/returntoflight/system/system_SRB.html \| title = Solid Rocket Boosters \| publisher = NASA \| access-date = 2015-10-02 \| archive-date = 2013-04-06 \| archive-url = https://web.archive.org/web/20130406193019/http://www.nasa.gov/returntoflight/system/system_SRB.html \| url-status = dead }}</ref> It developed a specific impulse of 242 seconds (2.37 km/s) at sea level or 268 seconds (2.63 km/s) in a vacuum. The 2005–2009 [[Constellation Program]] was to use a similar PBAN-bound APCP.<ref>{{cite news \|title=NASA Tests Engine With an Uncertain Future \|url=https://www.nytimes.com/2010/08/31/science/space/31rocket.html?hpw \|work=[[New York Times]] \|date=August 30, 2010 \|access-date=2010-08-31 \| first=Kenneth \| last=Chang}}</ref>

	In 2009, a group succeeded in creating a propellant of [[water]] and nanoaluminium ([[ALICE (propellant)\|ALICE]]).		In 2009, a group succeeded in creating a propellant of [[water]] and nanoaluminium ([[ALICE (propellant)\|ALICE]]).

			==== "Candy" propellants ====
			In general, [[rocket candy]] propellants are an oxidizer (typically potassium nitrate) and a sugar fuel (typically [[dextrose]], [[sorbitol]], or [[sucrose]]) that are cast into shape by gently melting the propellant constituents together and pouring or packing the [[amorphous]] [[colloid]] into a mold. Candy propellants generate a low-medium specific impulse of roughly {{convert\|130\|isp\|abbr=on}} and, thus, are used primarily by amateur and experimental rocketeers.

	===High-energy composite (HEC) propellants===		===High-energy composite (HEC) propellants===
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	Electric solid propellants (ESPs) are a family of high performance [[plastisol]] solid propellants that can be ignited and throttled by the application of electric current. Unlike conventional rocket motor propellants that are difficult to control and extinguish, ESPs can be ignited reliably at precise intervals and durations. It requires no moving parts and the propellant is insensitive to flames or electrical sparks.<ref>{{cite book\|chapter-url=http://arc.aiaa.org/doi/abs/10.2514/6.2013-4168\|chapter=Electrical Solid Propellants: A Safe, Micro to Macro Propulsion Technology\|first1=Wayne N.\|last1=Sawka\|first2=Michael\|last2=McPherson\|title=49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference\|date=12 July 2013\|publisher=American Institute of Aeronautics and Astronautics\|doi=10.2514/6.2013-4168\|isbn=978-1-62410-222-6}}</ref>		Electric solid propellants (ESPs) are a family of high performance [[plastisol]] solid propellants that can be ignited and throttled by the application of electric current. Unlike conventional rocket motor propellants that are difficult to control and extinguish, ESPs can be ignited reliably at precise intervals and durations. It requires no moving parts and the propellant is insensitive to flames or electrical sparks.<ref>{{cite book\|chapter-url=http://arc.aiaa.org/doi/abs/10.2514/6.2013-4168\|chapter=Electrical Solid Propellants: A Safe, Micro to Macro Propulsion Technology\|first1=Wayne N.\|last1=Sawka\|first2=Michael\|last2=McPherson\|title=49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference\|date=12 July 2013\|publisher=American Institute of Aeronautics and Astronautics\|doi=10.2514/6.2013-4168\|isbn=978-1-62410-222-6}}</ref>

	==Hobby and amateur rocketry==		==Hobby and amateur/model rocketry==
	Solid propellant rocket motors can be bought for use in [[model rocket]]ry; they are normally small cylinders of black powder fuel with an integral [[nozzle]] and optionally a small charge that is set off when the propellant is exhausted after a time delay. This charge can be used to trigger a [[camera]], or deploy a [[parachute]]. Without this charge and delay, the motor may ignite a second [[multistage rocket\|stage]] (black powder only).		Solid propellant rocket motors can be bought for use in [[model rocket]]ry; they are normally small cylinders of black powder fuel with an integral [[nozzle]] and optionally a small charge that is set off when the propellant is exhausted after a time delay. This charge can be used to trigger a [[camera]], or deploy a [[parachute]]. Without this charge and delay, the motor may ignite a second [[multistage rocket\|stage]] (black powder only).

			In [[amateur rocketry]], "candy" propellants are common because they offer relative safety and ease of production, ingredients that are readily available publicly, and a higher specific impulse than blackpowder motors.

	In mid- and [[high-power rocketry]], commercially made APCP motors are widely used. They can be designed as either single-use or reloadables. These motors are available in impulse ranges from "A" (1.26 Ns– 2.50 Ns) to "O" (20.48 kNs – 40.96 kNs), from several manufacturers. They are manufactured in standardized diameters and varying lengths depending on required impulse. Standard motor diameters are 13, 18, 24, 29, 38, 54, 75, 98, and 150 millimeters. Different propellant formulations are available to produce different thrust profiles, as well as special effects such as colored flames, smoke trails, or large quantities of sparks (produced by adding [[titanium]] sponge to the mix).		In mid- and [[high-power rocketry]], commercially made APCP motors are widely used. They can be designed as either single-use or reloadables. These motors are available in impulse ranges from "A" (1.26 Ns– 2.50 Ns) to "O" (20.48 kNs – 40.96 kNs), from several manufacturers. They are manufactured in standardized diameters and varying lengths depending on required impulse. Standard motor diameters are 13, 18, 24, 29, 38, 54, 75, 98, and 150 millimeters. Different propellant formulations are available to produce different thrust profiles, as well as special effects such as colored flames, smoke trails, or large quantities of sparks (produced by adding [[titanium]] sponge to the mix).
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	* [[Omega (rocket)\|OmegA]] (project was cancelled in 2020, rocket unflown)		* [[Omega (rocket)\|OmegA]] (project was cancelled in 2020, rocket unflown)
	* [[Qaem 100]]		* [[Qaem 100]]
			* [[Gravity-1]]
	{{colend}}		{{colend}}

			Gravity-1 is the largest-payload-capacity rocket to get into orbit with only solid rocket motors.

	Larger liquid-fueled orbital rockets often use solid rocket boosters to gain enough initial thrust to launch the fully fueled rocket.		Larger liquid-fueled orbital rockets often use solid rocket boosters to gain enough initial thrust to launch the fully fueled rocket.
	{{Main\|Solid rocket booster}}		{{Main\|Solid rocket booster}}
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	* [[Ariane 5]]		* [[Ariane 5]]
	* [[Atlas II]]		* [[Atlas II]]
	* [[Atlas V]] (optionally ~~1-5~~ boosters)		* [[Atlas V]] (optionally 1–5 boosters)
	* [[Delta IV]] (optionally 2 or 4 boosters)		* [[Delta IV]] (optionally 2 or 4 boosters)
	* [[H-IIA]], [[H-IIB]]		* [[H-IIA]], [[H-IIB]]
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	{{DEFAULTSORT:Solid-Fuel Rocket}}		{{DEFAULTSORT:Solid-Fuel Rocket}}
			[[Category:Aviation technology]]
	[[Category:Chinese inventions]]		[[Category:Chinese inventions]]
	[[Category:Rocket engines]]		[[Category:Rocket engines]]

2A02:AB88:3809:A800:6F3D:ABBE:7A31:C3CF: /* Grain geometry */ fixed typo

2025-04-28T22:21:33Z

Grain geometry: fixed typo

Show changes

← Previous revision		Revision as of 02:14, 13 December 2025
Line 32:		Line 32:
	[[File:RIAN archive 303890 A battery of Katyusha during the 1941-1945 Great Patriotic War.jpg\|thumb\|A battery of [[Katyusha rocket launcher]]s fires at German forces during the [[Battle of Stalingrad]], 6 October 1942]]		[[File:RIAN archive 303890 A battery of Katyusha during the 1941-1945 Great Patriotic War.jpg\|thumb\|A battery of [[Katyusha rocket launcher]]s fires at German forces during the [[Battle of Stalingrad]], 6 October 1942]]
	[[File:Aerojet260.png\|thumb\|Aerojet 260 motor test, 25 September 1965]]		[[File:Aerojet260.png\|thumb\|Aerojet 260 motor test, 25 September 1965]]
	The medieval [[Song dynasty]] Chinese invented ~~a very primitive form of~~ solid-propellant rocket.<ref>{{Cite book \|title=Space Science in China \|last= Hu \|first=Wen-Rui \|year=1997 \|isbn= 978-9056990237 \|publication-date=August 20, 1997 \|page=15\|publisher= CRC Press }}</ref> Illustrations and descriptions in the 14th century Chinese military treatise ''[[Huolongjing]]'' by the Ming dynasty military writer and philosopher [[Jiao Yu]] confirm that the Chinese in 1232 used ~~proto~~ solid propellant rockets then known as "[[fire arrows]]" to drive back the Mongols during the [[Siege of Kaifeng (1232)]].<ref name="Greatrix 2012 1">{{Cite book \|title=Powered Flight: The Engineering of Aerospace Propulsion \|last=Greatrix \|first= David R. \|publisher=Springer \|year=2012 \|isbn=978-1447124849 \|pages=1}}</ref><ref name="Nielsen 1997 2–4">{{Cite book \|title=Blast Off!: Rocketry for Elementary and Middle School Students P \|last= Nielsen \|first= Leona \|publisher= Libraries Unlimited \|year=1997 \|isbn= 978-1563084386 \|pages=2–4}}</ref> Each arrow took ~~a primitive~~ form of a simple, solid-propellant rocket tube that was filled with gunpowder. One open end allowed the gas to escape and was attached to a long stick that acted as a guidance system for flight direction control.<ref name="Nielsen 1997 2–4"/><ref name="Greatrix 2012 1"/>		The medieval [[Song dynasty]] Chinese invented the solid-propellant rocket.<ref>{{Cite book \|title=Space Science in China \|last= Hu \|first=Wen-Rui \|year=1997 \|isbn= 978-9056990237 \|publication-date=August 20, 1997 \|page=15\|publisher= CRC Press }}</ref> Illustrations and descriptions in the 14th century Chinese military treatise ''[[Huolongjing]]'' by the Ming dynasty military writer and philosopher [[Jiao Yu]] confirm that the Chinese in 1232 used solid propellant rockets then known as "[[fire arrows]]" to drive back the Mongols during the [[Siege of Kaifeng (1232)]].<ref name="Greatrix 2012 1">{{Cite book \|title=Powered Flight: The Engineering of Aerospace Propulsion \|last=Greatrix \|first= David R. \|publisher=Springer \|year=2012 \|isbn=978-1447124849 \|pages=1}}</ref><ref name="Nielsen 1997 2–4">{{Cite book \|title=Blast Off!: Rocketry for Elementary and Middle School Students P \|last= Nielsen \|first= Leona \|publisher= Libraries Unlimited \|year=1997 \|isbn= 978-1563084386 \|pages=2–4}}</ref> Each arrow took the form of a simple, solid-propellant rocket tube that was filled with gunpowder. One open end allowed the gas to escape and was attached to a long stick that acted as a guidance system for flight direction control.<ref name="Nielsen 1997 2–4"/><ref name="Greatrix 2012 1"/>

	The first rockets with tubes of cast iron were used by the [[Kingdom of Mysore]] under [[Hyder Ali]] and [[Tipu Sultan]] in the 1750s. These rockets had a reach of targets up to a mile and a half away. These were extremely effective in the [[Second Anglo-Mysore War]] that ended in a humiliating defeat for the [[British East India Company]]. Word of the success of the Mysore rockets against the British triggered research in England, France, Ireland and elsewhere. When the British finally conquered the fort of [[Siege of Seringapatam (1799)\|Srirangapatana]] in 1799, hundreds of rockets were shipped off to the [[Royal Arsenal]] near London to be reverse-engineered. This led to the first industrial manufacture of military rockets with the [[Congreve rocket]] in 1804.<ref name="Bowdoin 2004">{{Cite book \|title=Rockets and Missiles: The Life Story of a Technology\|last= Van Riper \|first= Bowdoin \|publisher= The Johns Hopkins University Press \|year=2004 \|isbn= 978-0801887925 \|pages=14–15}}</ref>		The first rockets with tubes of cast iron were used by the [[Kingdom of Mysore]] under [[Hyder Ali]] and [[Tipu Sultan]] in the 1750s. These rockets had a reach of targets up to a mile and a half away. These were extremely effective in the [[Second Anglo-Mysore War]] that ended in a humiliating defeat for the [[British East India Company]]. Word of the success of the Mysore rockets against the British triggered research in England, France, Ireland and elsewhere. When the British finally conquered the fort of [[Siege of Seringapatam (1799)\|Srirangapatana]] in 1799, hundreds of rockets were shipped off to the [[Royal Arsenal]] near London to be reverse-engineered. This led to the first industrial manufacture of military rockets with the [[Congreve rocket]] in 1804.<ref name="Bowdoin 2004">{{Cite book \|title=Rockets and Missiles: The Life Story of a Technology\|last= Van Riper \|first= Bowdoin \|publisher= The Johns Hopkins University Press \|year=2004 \|isbn= 978-0801887925 \|pages=14–15}}</ref>