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Hydroxylammonium nitrate

From Wikipedia, the free encyclopedia
Hydroxylammonium nitrate
Names
Other names
hydroxylamine nitrate
Identifiers
3D model (JSmol)
ChemSpider
ECHA InfoCard 100.033.342 Edit this at Wikidata
EC Number
  • 236-691-2
  • InChI=1S/NO3.H4NO/c2-1(3)4;1-2/h;2H,1H3/q-1;+1 checkY
    Key: CRJZNQFRBUFHTE-UHFFFAOYSA-N checkY
  • InChI=1/NO3.H4NO/c2-1(3)4;1-2/h;2H,1H3/q-1;+1
    Key: CRJZNQFRBUFHTE-UHFFFAOYAP
  • [NH3+]O.[N+](=O)([O-])[O-]
Properties
[NH3OH]+[NO3]−
Molar mass 96.04 g/mol
Density 1.84 g/cm3
Melting point 48 °C
Soluble
Hazards
GHS labelling:
GHS01: ExplosiveGHS06: ToxicGHS07: Exclamation markGHS08: Health hazardGHS09: Environmental hazard
Danger
H201, H302, H311, H315, H317, H319, H351, H373, H400
P201, P202, P210, P230, P240, P250, P260, P261, P264, P270, P272, P273, P280, P281, P301+P312, P302+P352, P305+P351+P338, P308+P313, P312, P314, P321, P322, P330, P332+P313, P333+P313, P337+P313, P361, P362, P363, P370+P380, P372, P373, P391, P401, P405, P501
Safety data sheet (SDS) External MSDS (as 18 % solution)
Related compounds
Other anions
 Hydroxylammonium sulfate
Hydroxylammonium chloride
Other cations
 Ammonium nitrate
Related compounds
 Hydroxylamine
Except where otherwise noted, data are given for materials in their standard state (at 25 °C [77 °F], 100 kPa).
checkY verify (what is checkY☒N ?)

Hydroxylammonium nitrate or hydroxylamine nitrate (HAN) is an inorganic compound with the chemical formula [NH3OH]+[NO3]−. It is a salt derived from hydroxylamine and nitric acid. In its pure form, it is a colourless hygroscopic solid. It has potential to be used as a rocket propellant either as a solution in monopropellants or bipropellants.[1] Hydroxylammonium nitrate (HAN)-based propellants are a viable and effective solution for future "green" propellant-based missions, as it offers 50% higher performance for a given propellant tank compared to commercially used hydrazine.

Properties

[edit]

The compound is a salt with separated hydroxyammonium and nitrate ions.[2] Hydroxylammonium nitrate is unstable because it contains both a reducing agent (hydroxylammonium cation) and an oxidizer (nitrate),[3] the situation being analogous to ammonium nitrate. It is usually handled as an aqueous solution with small amount of nitric acid as a stabilizer.[4]: 1641  The solution is corrosive and toxic, and may be carcinogenic. Solid HAN is unstable, especially in the presence of trace amounts of iron(III).

Laboratory preparatory routes

[edit]
  1. Catalytic reduction of nitric oxides
  2. Double decomposition
  3. Electrolysis
  4. Hydrogenation of nitric acid
  5. Ion exchange via resins
  6. Neutralization

Applications

[edit]

HAN has applications as a component of rocket propellant, in both solid and liquid form. HAN and ammonium dinitramide (ADN), another energetic ionic compound, were investigated as less-toxic replacements for toxic hydrazine for monopropellant rockets where only a catalyst is needed to cause decomposition.[5] HAN and ADN will work as monopropellants in water solution, as well as when dissolved with fuel liquids such as methanol.

HAN is used by the Network Centric Airborne Defense Element boost-phase interceptor being developed by Raytheon.[6] As a solid propellant oxidizer, it is typically bonded with glycidyl azide polymer (GAP), hydroxyl-terminated polybutadiene (HTPB), or carboxy-terminated polybutadiene (CTPB) and requires preheating to 200-300 °C to decompose.[citation needed] When used as a monopropellant, the catalyst is a noble metal, similar to the other monopropellants that use silver, palladium, or iridium.[citation needed]

HAN also enabled the development of solid propellants that could be controlled electrically and switched on and off.[7] Developed by DSSP for special effects[8] and microthrusters, these were the first HAN-based propellants in space; and aboard the Naval Research Laboratory SpinSat, launched in 2014.[9][10]

It was used in a fuel/oxidizer blend known as "AF-M315E"[1] in the high thrust engines of the Green Propellant Infusion Mission,[11][12][13] which was initially expected to be launched in 2015, and eventually launched and deployed on 25 June 2019.[14] The specific impulse of AF-M315E is 257 s.[1] The aqueous solution of HAN can be added with fuel components such as methanol, glycine, TEAN (triethanolammonium nitrate), and amines to form high performance monopropellants for space propulsion systems.[15]

China Aerospace Science and Technology Corporation (CASC) launched a demonstration of HAN-based thruster aboard a microsatellite in January 2018.[16]

Japanese technology demonstration satellite Innovative Satellite Technology Demonstration-1, launched in January 2019, contains a demonstration thruster using HAN and operated successfully in orbit.[17][18][19]

HAN is sometimes used in nuclear reprocessing as a reducing agent for plutonium ions.[20]

Bibliography

[edit]
  • Donald G. Harlow et al. (1998). "Technical Report on Hydroxlyamine Nitrate". U.S. Department of Energy. DOE/EH-0555
  • Gösta Bengtsson et al. (2002) "The kinetics and mechanism of oxidation of hydroxylamine by iron(III)". J. Chem. Soc., Dalton Trans., 2002, 2548–2552. doi:10.1039/B201602H
  • Schmidt, Eckart W. (2022). "Hydroxylammonium Salts". Encyclopedia of Oxidizers. Vol. 3. De Gruyter. pp. 1589–1816. doi:10.1515/9783110750294-011. ISBN 978-3-11-075029-4.
  • Schmidt, Eckart W. (2023). "Hydroxylammonium Nitrate-Based Monopropellants". Encyclopedia of Monopropellants. Vol. 2. De Gruyter. pp. 807–1194. doi:10.1515/9783110751390-007. ISBN 978-3-11-075139-0.

References

[edit]
  1. ^ a b c Spores, Ronald A.; Masse, Robert; Kimbrel, Scott; McLean, Chris (15–17 July 2013). "GPIM AF-M315E Propulsion System" (PDF). San Jose, California, USA: 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Archived (PDF) from the original on 2014-02-28.
  2. ^ Rheingold, A. L.; Cronin, J. T.; Brill, T. B.; Ross, F. K. (March 1987). "Structure of hydroxylammonium nitrate (HAN) and the deuterium homolog". Acta Crystallographica Section C. 43 (3): 402–404. Bibcode:1987AcCrC..43..402R. doi:10.1107/S0108270187095593.
  3. ^ Pembridge, John R.; Stedman, Geoffrey (1979). "Kinetics, mechanism, and stoicheiometry of the oxidation of hydroxylamine by nitric acid". Journal of the Chemical Society, Dalton Transactions (11): 1657–1663. doi:10.1039/dt9790001657. ISSN 0300-9246.
  4. ^ Schmidt, Eckart W. (2022). "Hydroxylammonium Salts". Encyclopedia of Oxidizers. Vol. 3. De Gruyter. pp. 1589–1816. doi:10.1515/9783110750294-011. ISBN 978-3-11-075029-4.
  5. ^ Dominic Freudenmann; Helmut K. Ciezki (29 July 2019). "ADN and HAN-Based Monopropellants – A Minireview on Compatibility and Chemical Stability in Aqueous Media". Propellants, Explosives, Pyrotechnics. 44 (9). Wiley Online Library: 1084–1089. doi:10.1002/prep.201900127.
  6. ^ "Boost phase interceptor". Press Releases. Raytheon. Archived from the original on May 18, 2007.
  7. ^ Sawka, Wayne N.; McPherson, Michael (2013-07-12), "Electrical Solid Propellants: A Safe, Micro to Macro Propulsion Technology", 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Joint Propulsion Conferences, American Institute of Aeronautics and Astronautics, doi:10.2514/6.2013-4168, ISBN 978-1-62410-222-6
  8. ^ "LDI 2014 Award Winners Announced". Live Design Online. 2014-11-23. Retrieved 2019-06-19.
  9. ^ Nicholas, Andrew; Finne, Ted; Gaylsh, Ivan; Mai, Anthony; Yen, Jim (September 2013). "SpinSat Mission Overview" (PDF). Archived (PDF) from the original on June 19, 2019.
  10. ^ "SpinSat - Satellite Missions - eoPortal Directory". directory.eoportal.org. Retrieved 2019-06-19.
  11. ^ "About Green Propellant Infusion Mission (GPIM)". NASA. 2014. Archived from the original on 2013-04-24.
  12. ^ "Green Propellant Infusion Mission (GPIM)". Ball Aerospace. 2014. Archived from the original on 2013-04-24.
  13. ^ Casey, Tina (19 July 2013). "NASA Sets Its Sights On $45 Million Green Fuel Mission". Clean Technica.
  14. ^ Sempsrott, Danielle (25 June 2019). "NASA's Green Propellant Infusion Mission Deploys". NASA. Retrieved 6 June 2020.
  15. ^ Wucherer, E.; Christofferson, Stacy; Reed, Brian (2000). Assessment of high performance HAN-monopropellants. 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. doi:10.2514/6.2000-3872.
  16. ^ 航天科技六院801所HAN 基无毒推进发动机研制攻关记 [HAN-based non-toxic propulsion engine research and development of 801 Institute of the Sixth Academy of Space Science and Technology] (in Chinese (China)). China Aerospace Science and Technology Corporation. 24 May 2019. Retrieved 14 May 2020.
  17. ^ "革新的衛星技術実証1号機 PRESS KIT" [Innovative Satellite Technology Demonstration Flight No. 1 PRESS KIT] (PDF). JAXA. Retrieved 15 March 2019.
  18. ^ 小型実証衛星1号機 RAPIS-1 グリーンプロペラント推進系（GPRCS）世界初の軌道上 HAN系推進薬 実証！ [Small Demonstration Satellite-1 RAPIS-1 Green Propellant Reaction Control System (GPRCS), the world's first on-orbit HAN propulsion system demonstration!] (in Japanese). JAXA. 15 March 2019. Retrieved 15 March 2019.
  19. ^ Hori, Keiichi; Katsumi, Toshiyuki; Sawai, Shujiro; Azuma, Nobuyuki; Hatai, Keigo; Nakatsuka, Junichi (2019). "HAN-Based Green Propellant, SHP163 – Its R&D and Test in Space". Propellants, Explosives, Pyrotechnics. 44 (9): 1080–1083. doi:10.1002/prep.201900237. ISSN 0721-3115.
  20. ^ McKibben, J. M.; Bercaw, J. E. (1971-01-01). Hydroxylamine nitrate as a plutonium reductant in the PUREX solvent extraction process (Technical report). Du Pont de Nemours (E. I.) and Co., Aiken, S. C. Savannah River Lab. doi:10.2172/4065655. DP-1248.
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