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Saturday, November 19, 2022

Hydrazine

From Wikipedia, the free encyclopedia
https://en.wikipedia.org/wiki/Hydrazine

Hydrazine
Skeletal formula of hydrazine with all explicit hydrogens added
Spacefill model of hydrazine
Stereo, skeletal formula of hydrazine with all explicit hydrogens added
Ball and stick model of hydrazine
Sample of hydrazine hydrate.jpg
Hydrazine hydrate
Names
IUPAC name
Hydrazine
Systematic IUPAC name
Diazane
Other names
Diamine
Tetrahydridodinitrogen(N-N)
Diamidogen
Identifiers
3D model (JSmol)
3DMet
878137
ChEBI
ChEMBL
ChemSpider
ECHA InfoCard 100.005.560 Edit this at Wikidata
EC Number
  • 206-114-9
190
KEGG
MeSH Hydrazine
RTECS number
  • MU7175000
UNII
UN number 2029


Properties
N2H4
Molar mass 32.0452 g/mol
Appearance Colorless, fuming, oily liquid
Odor Ammonia-like
Density 1.021 g/cm3
Melting point 2 °C; 35 °F; 275 K
Boiling point 114 °C; 237 °F; 387 K
Miscible
log P 0.67
Vapor pressure 1 kPa (at 30.7 °C)
Acidity (pKa) 8.10 ([N2H5]+)
Basicity (pKb) 5.90
Conjugate acid Hydrazinium
1.46044 (at 22 °C)
Viscosity 0.876 cP
Structure
Triangular pyramidal at N
1.85 D
Thermochemistry
121.52 J/(K·mol)
50.63 kJ/mol
Hazards
GHS labelling:
GHS02: Flammable GHS05: Corrosive GHS06: Toxic GHS08: Health hazard GHS09: Environmental hazard
Danger
H226, H301, H311, H314, H317, H331, H350, H410
P201, P261, P273, P280, P301+P310, P305+P351+P338
NFPA 704 (fire diamond)
4
2
3
Flash point 52 °C (126 °F; 325 K)
24 to 270 °C (75 to 518 °F; 297 to 543 K)
Explosive limits 1.8–99.99%
Lethal dose or concentration (LD, LC):
59–60 mg/kg (oral in rats, mice)
260 ppm (rat, 4 hr)
630 ppm (rat, 1 hr)
570 ppm (rat, 4 hr)
252 ppm (mouse, 4 hr)
NIOSH (US health exposure limits):
PEL (Permissible)
TWA 1 ppm (1.3 mg/m3) [skin]
REL (Recommended)
Ca C 0.03 ppm (0.04 mg/m3) [2-hour]
IDLH (Immediate danger)
Ca [50 ppm]
Safety data sheet (SDS) ICSC 0281
Related compounds
Other anions
Tetrafluorohydrazine
Hydrogen peroxide
Diphosphane
Diphosphorus tetraiodide
Other cations
Organic hydrazines
Related Binary azanes
Ammonia
Triazane
Related compounds
Diazene
Triazene
Tetrazene
Diphosphene
Except where otherwise noted, data are given for materials in their standard state (at 25 °C [77 °F], 100 kPa).

Hydrazine is an inorganic compound with the chemical formula N2H4. It is a simple pnictogen hydride, and is a colourless flammable liquid with an ammonia-like odour. It is not dissimilar to Diazene or Triazene and, although its name might suggest otherwise, very dissimilar to Triazine and Tetrazine.

Hydrazine is highly toxic unless handled in solution as, for example, hydrazine hydrate (N2H4·xH2O). As of 2015, the world hydrazine hydrate market amounted to $350 million. Hydrazine is mainly used as a foaming agent in preparing polymer foams, but applications also include its uses as a precursor to polymerization catalysts, pharmaceuticals, and agrochemicals, as well as a long-term storable propellant for in-space spacecraft propulsion.

About two million tons of hydrazine hydrate were used in foam blowing agents in 2015. Additionally, hydrazine is used in various rocket fuels and to prepare the gas precursors used in air bags. Hydrazine is used within both nuclear and conventional electrical power plant steam cycles as an oxygen scavenger to control concentrations of dissolved oxygen in an effort to reduce corrosion.

Hydrazines refer to a class of organic substances derived by replacing one or more hydrogen atoms in hydrazine by an organic group.

Etymology

The nomenclature is a bi-valent form, with prefix hydr- used to indicate the presence of hydrogen atoms and suffix beginning with -az-, from the francised root azote, used to indicate the presence of nitrogen.

Uses

Gas producers and propellants

The largest use of hydrazine is as a precursor to blowing agents. Specific compounds include azodicarbonamide and azobisisobutyronitrile, which produce 100–200 mL of gas per gram of precursor. In a related application, sodium azide, the gas-forming agent in air bags, is produced from hydrazine by reaction with sodium nitrite.

Hydrazine is also used as a long-term storable propellant on board space vehicles, such as the Dawn mission to Ceres and Vesta, and to both reduce the concentration of dissolved oxygen in and control pH of water used in large industrial boilers. The F-16 fighter jet, Eurofighter Typhoon, Space Shuttle, and U-2 spy plane use hydrazine to fuel their Emergency Start System in the event of an engine stall.

Precursor to pesticides and pharmaceuticals

Fluconazole, synthesized using hydrazine, is an antifungal medication.

Hydrazine is a precursor to several pharmaceuticals and pesticides. Often these applications involve conversion of hydrazine to heterocyclic rings such as pyrazoles and pyridazines. Examples of commercialized bioactive hydrazine derivatives include cefazolin, rizatriptan, anastrozole, fluconazole, metazachlor, metamitron, metribuzin, paclobutrazol, diclobutrazole, propiconazole, hydrazine sulfate, diimide, triadimefon, and dibenzoylhydrazine.

Hydrazine compounds can be effective as active ingredients in admixture with or in combination with other agricultural chemicals such as insecticides, miticides, nematicides, fungicides, antiviral agents, attractants, herbicides or plant growth regulators.

Small-scale, niche, and research

The Italian catalyst manufacturer Acta (chemical company) has proposed using hydrazine as an alternative to hydrogen in fuel cells. The chief benefit of using hydrazine is that it can produce over 200 mW/cm2 more than a similar hydrogen cell without the need to use expensive platinum catalysts. Because the fuel is liquid at room temperature, it can be handled and stored more easily than hydrogen. By storing the hydrazine in a tank full of a double-bonded carbon-oxygen carbonyl, the fuel reacts and forms a safe solid called hydrazone. By then flushing the tank with warm water, the liquid hydrazine hydrate is released. Hydrazine has a higher electromotive force of 1.56 V compared to 1.23 V for hydrogen. Hydrazine breaks down in the cell to form nitrogen and hydrogen which bonds with oxygen, releasing water. Hydrazine was used in fuel cells manufactured by Allis-Chalmers Corp., including some that provided electric power in space satellites in the 1960s.

A mixture of 63% hydrazine, 32% hydrazine nitrate and 5% water is a standard propellant for experimental bulk-loaded liquid propellant artillery. The propellant mixture above is one of the most predictable and stable, with a flat pressure profile during firing. Misfires are usually caused by inadequate ignition. The movement of the shell after a mis-ignition causes a large bubble with a larger ignition surface area, and the greater rate of gas production causes very high pressure, sometimes including catastrophic tube failures (i.e. explosions). From January–June 1991, the U.S. Army Research Laboratory conducted a review of early bulk-loaded liquid propellant gun programs for possible relevance to the electrothermal chemical propulsion program.

The United States Air Force (USAF) regularly uses H-70, a 70% hydrazine 30% water mixture, in operations employing the General Dynamics F-16 “Fighting Falcon” fighter aircraft and the Lockheed U-2 “Dragon Lady” reconnaissance aircraft. The single jet engine F-16 utilizes hydrazine to power its Emergency Power Unit (EPU), which provides emergency electrical and hydraulic power in the event of an engine flame out. The EPU activates automatically, or manually by pilot control, in the event of loss of hydraulic pressure or electrical power in order to provide emergency flight controls. The single jet engine U-2 utilizes hydrazine to power its Emergency Starting System (ESS), which provides a highly reliable method to restart the engine in flight in the event of a stall.

Rocket fuel

Anhydrous (pure, not in solution) hydrazine being loaded into the MESSENGER space probe. The technician is wearing a safety suit.

Hydrazine was first used as a component in rocket fuels during World War II. A 30% mix by weight with 57% methanol (named M-Stoff in the German Luftwaffe) and 13% water was called C-Stoff by the Germans. The mixture was used to power the Messerschmitt Me 163B rocket-powered fighter plane, in which the German high test peroxide T-Stoff was used as an oxidizer. Unmixed hydrazine was referred to as B-Stoff by the Germans, a designation also used later for the ethanol/water fuel for the V-2 missile.

Hydrazine is used as a low-power monopropellant for the maneuvering thrusters of spacecraft, and was used to power the Space Shuttle's auxiliary power units (APUs). In addition, mono-propellant hydrazine-fueled rocket engines are often used in terminal descent of spacecraft. Such engines were used on the Viking program landers in the 1970s as well as the Mars landers Phoenix (May 2008), Curiosity (August 2012) and Perseverance (February 2021).

A mixture of hydrazine and red fuming nitric acid was used in the Soviet space program where it was known as devil's venom due to its dangerous nature.

In all hydrazine mono-propellant engines, the hydrazine is passed over a catalyst such as iridium metal supported by high-surface-area alumina (aluminium oxide), which causes it to decompose into ammonia, nitrogen gas, and hydrogen gas according to the following reactions:

  1. N2H4 → N2 + 2 H2
  2. 3 N2H4 → 4 NH3 + N2
  3. 4 NH3 + N2H4 → 3 N2 + 8 H2

The first two reactions are extremely exothermic (the catalyst chamber can reach 800 °C in a matter of milliseconds,) and they produce large volumes of hot gas from a small volume of liquid, making hydrazine a fairly efficient thruster propellant with a vacuum specific impulse of about 220 seconds. Reaction 2 is the most exothermic, but produces a smaller number of molecules than that of reaction 1. Reaction 3 is endothermic and reverts the effect of reaction 2 back to the same effect as reaction 1 alone (lower temperature, greater number of molecules). The catalyst structure affects the proportion of the NH3 that is dissociated in reaction 3; a higher temperature is desirable for rocket thrusters, while more molecules are desirable when the reactions are intended to produce greater quantities of gas.

Since hydrazine is a solid below 2 °C, it is not suitable as a general purpose rocket propellant for military applications. Other variants of hydrazine that are used as rocket fuel are monomethylhydrazine, CH3NHNH2, also known as MMH (melting point −52 °C), and unsymmetrical dimethylhydrazine, (CH3)2NNH2, also known as UDMH (melting point −57 °C). These derivatives are used in two-component rocket fuels, often together with dinitrogen tetroxide, N2O4. A 50:50 mixture by weight of hydrazine and UDMH was used in the Titan II ICBMs and is known as Aerozine 50. These reactions are extremely exothermic, and the burning is also hypergolic (it starts burning without any external ignition).

There are ongoing efforts in the aerospace industry to replace hydrazine with its potential ban across the European union. Promising alternatives include nitrous oxide-based propellant combinations, with development being led by commercial companies Dawn Aerospace, Impulse Space, and Launcher. The first nitrous oxide-based system ever flown in space was by D-Orbit onboard their ION Satellite Carrier in 2021, using six Dawn Aerospace B20 thrusters.

Occupational hazards

Health effects

Potential routes of hydrazine exposure include dermal, ocular, inhalation and ingestion.

Hydrazine exposure can cause skin irritation/contact dermatitis and burning, irritation to the eyes/nose/throat, nausea/vomiting, shortness of breath, pulmonary edema, headache, dizziness, central nervous system depression, lethargy, temporary blindness, seizures and coma. Exposure can also cause organ damage to the liver, kidneys and central nervous system. Hydrazine is documented as a strong skin sensitizer with potential for cross-sensitization to hydrazine derivatives following initial exposure. In addition to occupational uses reviewed above, exposure to hydrazine is also possible in small amounts from tobacco smoke.

The official U.S. guidance on hydrazine as a carcinogen is mixed but generally there is recognition of potential cancer-causing effects. The National Institute for Occupational Safety and Health (NIOSH) lists it as a “potential occupational carcinogen”. The National Toxicology Program (NTP) finds it is "reasonably anticipated to be a human carcinogen". The American Conference of Governmental Industrial Hygienists (ACGIH) grades hydrazine as "A3—confirmed animal carcinogen with unknown relevance to humans". The U.S. Environmental Protection Agency (EPA) grades it as "B2—a probable human carcinogen based on animal study evidence".

The International Agency for Research on Cancer (IARC) rates hydrazine as "2A—probably carcinogenic to humans" with a positive association observed between hydrazine exposure and lung cancer. Based on cohort and cross-sectional studies of occupational hydrazine exposure, a committee from the National Academies of Sciences, Engineering and Medicine concluded that there is suggestive evidence of an association between hydrazine exposure and lung cancer, with insufficient evidence of association with cancer at other sites. The European Commission’s Scientific Committee on Occupational Exposure Limits (SCOEL) places hydrazine in carcinogen “group B—a genotoxic carcinogen”. The genotoxic mechanism the committee cited references hydrazine's reaction with endogenous formaldehyde and formation of a DNA-methylating agent.

In the event of a hydrazine exposure-related emergency, NIOSH recommends removing contaminated clothing immediately, washing skin with soap and water, and for eye exposure removing contact lenses and flushing eyes with water for at least 15 minutes. NIOSH also recommends anyone with potential hydrazine exposure to seek medical attention as soon as possible. There are no specific post-exposure laboratory or medical imaging recommendations, and the medical work-up may depend on the type and severity of symptoms. The World Health Organization (WHO) recommends potential exposures be treated symptomatically with special attention given to potential lung and liver damage. Past cases of hydrazine exposure have documented success with Pyridoxine (Vitamin B6) treatment.

Occupational exposure limits

  • NIOSH Recommended Exposure Limit (REL): 0.03 ppm (0.04 mg/m3) 2-hour ceiling
  • OSHA Permissible Exposure Limit (PEL): 1 ppm (1.3 mg/m3) 8-hour Time Weighted Average
  • ACGIH Threshold Limit Value (TLV): 0.01 ppm (0.013 mg/m3) 8-hour Time Weighted Average

The odour threshold for hydrazine is 3.7 ppm, thus if a worker is able to smell an ammonia-like odor then they are likely over the exposure limit. However, this odor threshold varies greatly and should not be used to determine potentially hazardous exposures.

For aerospace personnel, the USAF uses an emergency exposure guideline, developed by the National Academy of Science Committee on Toxicology, which is utilized for non-routine exposures of the general public and is called the Short-Term Public Emergency Exposure Guideline (SPEGL). The SPEGL, which does not apply to occupational exposures, is defined as the acceptable peak concentration for unpredicted, single, short-term emergency exposures of the general public and represents rare exposures in a worker's lifetime. For hydrazine the 1-hour SPEGL is 2 ppm, with a 24-hour SPEGL of 0.08 ppm.

Handling and medical surveillance

A complete surveillance programme for hydrazine should include systematic analysis of biologic monitoring, medical screening and morbidity/mortality information. The CDC recommends surveillance summaries and education be provided for supervisors and workers. Pre-placement and periodic medical screening should be conducted with specific focus on potential effects of hydrazine upon functioning of the eyes, skin, liver, kidneys, hematopoietic, nervous and respiratory systems.

Common controls used for hydrazine include process enclosure, local exhaust ventilation and personal protective equipment (PPE). Guidelines for hydrazine PPE include non-permeable gloves and clothing, indirect-vent splash resistant goggles, face shield and in some cases a respirator. The use of respirators for the handling of hydrazine should be the last resort as a method of controlling worker exposure. In cases where respirators are needed, proper respirator selection and a complete respiratory protection program consistent with OSHA guidelines should be implemented.

For USAF personnel, Air Force Occupational Safety and Health (AFOSH) Standard 48-8, Attachment 8 reviews the considerations for occupational exposure to hydrazine in missile, aircraft and spacecraft systems. Specific guidance for exposure response includes mandatory emergency shower and eyewash stations and a process for decontaminating protective clothing. The guidance also assigns responsibilities and requirements for proper PPE, employee training, medical surveillance and emergency response. USAF bases requiring the use of hydrazine generally have specific base regulations governing local requirements for safe hydrazine use and emergency response.

Molecular structure

Hydrazine has formula NH2NH2, or more clearly H2N−NH2, with two amine groups NH2 connected by a single bond between the two nitrogens. Each N−NH2 subunit is pyramidal. The N–N single bond distance is 1.45 Å (145 pm), and the molecule adopts a gauche conformation. The rotational barrier is twice that of ethane. These structural properties resemble those of gaseous hydrogen peroxide, which adopts a "skewed" anticlinal conformation, and also experiences a strong rotational barrier.

Synthesis and production

Diverse routes have been developed. The key step is the creation of the N–N single bond. The many routes can be divided into those that use chlorine oxidants (and generate salt) and those that do not.

Oxidation of ammonia via oxaziridines from peroxide

Hydrazine can be synthesized from ammonia and hydrogen peroxide with a ketone catalyst, in a procedure called the Peroxide process (sometimes called Pechiney-Ugine-Kuhlmann process, the Atofina–PCUK cycle, or ketazine process). The net reaction follows:

2 NH3 + H2O2 → N2H4 + 2 H2O

In this route, the ketone and ammonia first condense to give the imine, which is oxidised by hydrogen peroxide to the oxaziridine, a three-membered ring containing carbon, oxygen, and nitrogen. Next, the oxaziridine gives the hydrazone by treatment with ammonia, which process creates the nitrogen-nitrogen single bond. This hydrazone condenses with one more equivalent of ketone.

Pechiney-Ugine-Kuhlmann process.png

The resulting azine is hydrolyzed to give hydrazine and regenerate the ketone, methyl ethyl ketone:

Me(Et)C=N−N=C(Et)Me + 2 H2O → 2 Me(Et)C=O + N2H4

Unlike most other processes, this approach does not produce a salt as a by-product.

Chlorine-based oxidations

The Olin Raschig process, first announced in 1907, produces hydrazine from sodium hypochlorite (the active ingredient in many bleaches) and ammonia without the use of a ketone catalyst. This method relies on the reaction of monochloramine with ammonia to create the N–N single bond as well as a hydrogen chloride byproduct:

NH2Cl + NH3 → N2H4 + HCl

Related to the Raschig process, urea can be oxidized instead of ammonia. Again sodium hypochlorite serves as the oxidant. The net reaction is shown:

(NH2)2CO + NaOCl + 2 NaOH → N2H4 + H2O + NaCl + Na2CO3

The process generates significant by-products and is mainly practised in Asia.

The Bayer Ketazine Process is the predecessor to the peroxide process. It employs sodium hypochlorite as oxidant instead of hydrogen peroxide. Like all hypochlorite-based routes, this method produces an equivalent of salt for each equivalent of hydrazine.

Reactions

Acid-base behavior

Hydrazine forms a monohydrate N2H4·H2O that is denser (1.032 g/cm3) than the anhydrous form N2H4 (1.021 g/cm3). Hydrazine has basic (alkali) chemical properties comparable to those of ammonia:

N2H4 + H2O → [N2H5]+ + OH, Kb = 1.3 × 10−6, pKb = 5.9

(for ammonia Kb = 1.78 × 10−5)

It is difficult to diprotonate:

[N2H5]+ + H2O → [N2H6]2+ + OH, Kb = 8.4 × 10−16, pKb = 15

Redox reactions

Ideally, the combustion of hydrazine in oxygen produces nitrogen and water:

N2H4 + O2 → N2 + 2 H2O

An excess of oxygen gives oxides of nitrogen, including nitrogen monoxide and nitrogen dioxide:

N2H4 + 2 O2 → 2 NO + 2 H2O
N2H4 + 3 O2 → 2 NO2 + 2 H2O

The heat of combustion of hydrazine in oxygen (air) is 19.41 MJ/kg (8345 BTU/lb).

Hydrazine is a convenient reductant because the by-products are typically nitrogen gas and water. This property makes it useful as an antioxidant, an oxygen scavenger, and a corrosion inhibitor in water boilers and heating systems. It is also used to reduce metal salts and oxides to the pure metals in electroless nickel plating and plutonium extraction from nuclear reactor waste. Some colour photographic processes also use a weak solution of hydrazine as a stabilising wash, as it scavenges dye coupler and unreacted silver halides. Hydrazine is the most common and effective reducing agent used to convert graphene oxide (GO) to reduced graphene oxide (rGO) via hydrothermal treatment.

Hydrazinium salts

Hydrazine can be protonated to form various solid salts of the hydrazinium cation [N2H5]+, by treatment with mineral acids. A common salt is hydrazinium hydrogensulfate, [N2H5]+[HSO4]. Hydrazinium hydrogensulfate was investigated as a treatment of cancer-induced cachexia, but proved ineffective.

Double protonation gives the hydrazinium dication [N2H6]2+, of which various salts are known.

Organic chemistry

Hydrazines are part of many organic syntheses, often those of practical significance in pharmaceuticals (see applications section), as well as in textile dyes and in photography.

Hydrazine is used in the Wolff-Kishner reduction, a reaction that transforms the carbonyl group of a ketone into a methylene bridge (or an aldehyde into a methyl group) via a hydrazone intermediate. The production of the highly stable dinitrogen from the hydrazine derivative helps to drive the reaction.

Being bifunctional, with two amines, hydrazine is a key building block for the preparation of many heterocyclic compounds via condensation with a range of difunctional electrophiles. With 2,4-pentanedione, it condenses to give the 3,5-dimethylpyrazole. In the Einhorn-Brunner reaction hydrazines react with imides to give triazoles.

Being a good nucleophile, N2H4 can attack sulfonyl halides and acyl halides. The tosylhydrazine also forms hydrazones upon treatment with carbonyls.

Hydrazine is used to cleave N-alkylated phthalimide derivatives. This scission reaction allows phthalimide anion to be used as amine precursor in the Gabriel synthesis.

Hydrazone formation

Illustrative of the condensation of hydrazine with a simple carbonyl is its reaction with propanone to give the diisopropylidene hydrazine (acetone azine). The latter reacts further with hydrazine to yield the hydrazone:

2 (CH3)2CO + N2H4 → 2 H2O + ((CH3)2C=N)2
((CH3)2C=N)2 + N2H4 → 2 (CH3)2C=NNH2

The propanone azine is an intermediate in the Atofina-PCUK process. Direct alkylation of hydrazines with alkyl halides in the presence of base yields alkyl-substituted hydrazines, but the reaction is typically inefficient due to poor control on level of substitution (same as in ordinary amines). The reduction of hydrazones to hydrazines present a clean way to produce 1,1-dialkylated hydrazines.

In a related reaction, 2-cyanopyridines react with hydrazine to form amide hydrazides, which can be converted using 1,2-diketones into triazines.

Biochemistry

Hydrazine is the intermediate in the anaerobic oxidation of ammonia (anammox) process. It is produced by some yeasts and the open ocean bacterium anammox (Brocadia anammoxidans).

The false morel produces the poison gyromitrin which is an organic derivative of hydrazine that is converted to monomethylhydrazine by metabolic processes. Even the most popular edible "button" mushroom Agaricus bisporus produces organic hydrazine derivatives, including agaritine, a hydrazine derivative of an amino acid, and gyromitrin.

History

The name "hydrazine" was coined by Emil Fischer in 1875; he was trying to produce organic compounds that consisted of mono-substituted hydrazine. By 1887, Theodor Curtius had produced hydrazine sulfate by treating organic diazides with dilute sulfuric acid; however, he was unable to obtain pure hydrazine, despite repeated efforts. Pure anhydrous hydrazine was first prepared by the Dutch chemist Lobry de Bruyn in 1895.

Nitrous oxide fuel blend

From Wikipedia, the free encyclopedia

Nitrous oxide fuel blend propellants are a class of liquid rocket propellants that were intended in the early 2010s to be able to replace hydrazine as the standard storable rocket propellent in some applications.

In nitrous-oxide fuel blends, the fuel and oxidizer are blended and stored; this is sometimes referred to as a mixed monopropellant. Upon use, the propellant is heated or passed over a catalyst bed and the nitrous oxide decomposes into oxygen-rich gasses. Combustion then ensues. Special care is needed in the chemical formulation and engine design to prevent detonating the stored fuel.

Overview

The propellant used in a rocket engine plays an important role in both engine design and in design of the launch vehicle and related ground equipment to service the vehicle. Weight, energy density, cost, toxicity, risk of explosions, and other problems make it important for engineers to design rockets with appropriate propellants. The major classes of rocket fuels are:

A common fuel in small maneuvering thrusters is hydrazine. It is liquid at room temperature and, having a positive enthalpy of formation, can be used as a monopropellant to greatly simplify system design. But it is also extremely toxic and has a relatively high freezing point of +1C. It is also unstable, an inherent property of any substance with a positive enthalpy of formation.

Nitrous oxide can be used as an oxidizer with various fuels; it is popular mainly in hybrid rockets. It is far less toxic than hydrazine and has a much lower boiling point, though it can be liquified at room temperature under pressure. Like hydrazine it has a positive enthalpy of formation that makes it both potentially unstable and a viable monopropellant. It can be decomposed with a catalyst to produce a hot mixture of nitrogen and oxygen. When mixed with a fuel and stored before use, it becomes a mixed monopropellant.

History

German rocket scientists were experimenting with nitrous oxide fuel blends as early as 1937. Nitrous oxide fuel blends testing continued throughout World War II. The promise of high performance, greater range and lighter feed systems drove experimentation with blends of nitrous oxide and ammonia, which resulted in numerous explosions and demolished motors. The complexities involved in building propulsion systems that can safely handle nitrous oxide fuel blend monopropellants have been a deterrent to serious development.

Subsequent development of nitrous oxide fuel blends picked up again in the 2000s, and in 2011 an in-space flight test mission was planned. In the event, the flight test was cancelled. Innovative Space Propulsion Systems had announced plans to test the NOFBX mono-propellant on the NASA portion of the International Space Station (ISS), with an initial tentative flight date no earlier than 2012. NASA formally approved the mission to the ISS on a 2013 launch slot in May 2012. The mission had been slated to travel to the ISS in the unpressurized cargo compartment of a SpaceX Dragon spacecraft during one of the contracted NASA cargo re-supply missions in mid-2013. The "ISPS NOFBX Green Propellant Demonstration" will utilize a deep-throttling 100 pounds-force (440 N)-thrust-class engine burning NOFBX rocket engine that will be mounted to the outside the European Columbus module on the ISS, and had been expected to remain on-orbit for approximately one year while undergoing a "series of in-space performance tests."

NOFBX was a trademarked name for a proprietary nitrous oxide/fuel/emulsifier blended mono-propellant developed by Firestar Technologies. The NOFBX patent claimed a mixture of nitrous oxide as the oxidizer with ethane, ethene or acetylene as the fuel.[8] NOFBX has a higher specific impulse (Isp) and is less toxic than other monopropellants currently used in space applications, such as hydrazine. Flight testing of NOFBX engines had been planned on the International Space Station, but, in the event, did not go forward.

NOFBX had previously been used to fuel a reciprocating engine to power high-altitude, long-endurance drone aircraft under a DARPA contract. NOFBX was promoted by the company at the time as a "game changing" technology with the several characteristics that underline why safer monopropellants were of interest in the industry:

  • constituents are widely available from chemical suppliers, inexpensive and safe to handle
  • can be transported and handled without undue precautions or hazards
  • its end products (N
    2
    , CO, H
    2
    O
    , H
    2
    and CO
    2
    ) are all substantially less toxic than traditional long-duration storable monopropellants and produce no accumulated deposits or contamination; whereas hydrazine emits ammonia
  • hydrazine has an Isp of about 230 s; NOFBX was reported to have an Isp of 300 s
  • has better energy density, more than three times greater than hydrazine
  • is tolerant to a wide thermal range; storable at room temperature on the ground as well as in temperatures found in outer space
  • was projected to lower cost compared to existing propulsion systems of comparable performance
  • is a monopropellant, which significantly reduces the need for auxiliary hardware, saving cost, volume, and mass for launch systems
  • utilizes thrusters that run cooler, reducing thermal design challenges

Safety concerns

A 2008 AIAA paper on the decomposition of nitrous oxide has raised concerns about the safety risks of mixing hydrocarbons with nitrous oxide. By adding hydrocarbons, the energy barrier to an explosive decomposition event is lowered significantly.

Plasma propulsion engine

From Wikipedia, the free encyclopedia
https://en.wikipedia.org/wiki/Plasma_propulsion_engine

A thruster during test firing
 
Artist rendition of VASIMR plasma engine

A plasma propulsion engine is a type of electric propulsion that generates thrust from a quasi-neutral plasma. This is in contrast with ion thruster engines, which generate thrust through extracting an ion current from the plasma source, which is then accelerated to high velocities using grids/anodes. These exist in many forms (see electric propulsion). However, in the scientific literature, the term "plasma thruster" sometimes encompasses thrusters usually designated as "ion engines".

Plasma thrusters do not typically use high voltage grids or anodes/cathodes to accelerate the charged particles in the plasma, but rather use currents and potentials that are generated internally to accelerate the ions, resulting in a lower exhaust velocity given the lack of high accelerating voltages.

This type of thruster has a number of advantages. The lack of high voltage grids of anodes removes a possible limiting element as a result of grid ion erosion. The plasma exhaust is 'quasi-neutral', which means that positive ions and electrons exist in equal number, which allows simple ion-electron recombination in the exhaust to neutralize the exhaust plume, removing the need for an electron gun (hollow cathode). Such a thruster often generates the source plasma using radio frequency or microwave energy, using an external antenna. This fact, combined with the absence of hollow cathodes (which are sensitive to all but noble gases), allows the possibility of using this thruster on a variety of propellants, from argon to carbon dioxide air mixtures to astronaut urine.

Plasma engines are well-suited for interplanetary missions due to their high specific impulse.

Many space agencies developed plasma propulsion systems, including the European Space Agency, Iranian Space Agency and Australian National University, who co-developed a double layer thruster.

History

Some plasma engines have seen active flight time and use on missions. In 2011, NASA partnered with Busek to launch the first hall effect thruster aboard the Tacsat-2 satellite. The thruster was the satellite's main propulsion system. The company launched another hall effect thruster that year. In 2020, research on a plasma jet was published by Wuhan University. The thrust estimates published in that work, however, were subsequently shown to be almost nine times theoretically possible levels even if 100% of the input microwave power were converted to thrust. 

Ad Astra Rocket Company is developing the VASIMR. Canadian company Nautel is producing the 200 kW RF generators required to ionize the propellant. Some component tests and "Plasma Shoot" experiments are performed in a Liberia, Costa Rica laboratory. This project is led by former NASA astronaut Dr. Franklin Chang-Díaz (CRC-USA).

The Costa Rican Aerospace Alliance announced the development of exterior support for the VASIMR to be fitted outside the International Space Station. This phase of the plan to test the VASIMR in space was expected to be conducted in 2016.

Advantages

Plasma engines have a much higher specific impulse (Isp) value than most other types of rocket technology. The VASIMR thruster can be throttled for an impulse greater than 12000 s, and hall thrusters have attained ~2000 s. This is a significant improvement over the bipropellant fuels of conventional chemical rockets, which feature specific impulses ~450 s. With high impulse, plasma thrusters are capable of reaching relatively high speeds over extended periods of acceleration. Ex-astronaut Franklin Chang-Diaz claims the VASIMR thruster could send a payload to Mars in as little as 39 days while reaching a maximum velocity of 34 miles per second (55 km/s).

Certain plasma thrusters, such as the mini-helicon, are hailed for their simplicity and efficiency. Their theory of operation is relatively simple and can use a variety of gases, or combinations.

These qualities suggest that plasma thrusters have value for many mission profiles.

Drawbacks

Possibly the most significant challenge to the viability of plasma thrusters is the energy requirement. The VX-200 engine, for example, requires 200 kW electrical power to produce 5 N of thrust, or 40 kW/N. This power requirement may be met by fission reactors, but the reactor mass (including heat rejection systems) may prove prohibitive.

Another challenge is plasma erosion. While in operation the plasma can thermally ablate the walls of the thruster cavity and support structure, which can eventually lead to system failure.

Due to their extremely low thrust, plasma engines are not suitable for launch-to-Earth-orbit. On average, these rockets provide about 2 pounds of thrust maximum. Plasma thrusters are highly efficient in open space, but do nothing to offset the orbit expense of chemical rockets.

Engine types

Helicon plasma thrusters

Helicon plasma thrusters use low-frequency electromagnetic waves (Helicon waves) that exist inside plasma when exposed to a static magnetic field. An RF antenna that wraps around a gas chamber creates waves and excites the gas, creating plasma. The plasma is expelled at high velocity to produce thrust via acceleration strategies that require various combinations of electric and magnetic fields of ideal topology. They belong to the category of electrodeless thrusters. These thrusters support multiple propellants, making them useful for longer missions. They can be made out of simple materials including a glass soda bottle.

Magnetoplasmadynamic thrusters

Magnetoplasmadynamic thrusters (MPD) use the Lorentz force (a force resulting from the interaction between a magnetic field and an electric current) to generate thrust. The electric charge flowing through the plasma in the presence of a magnetic field causes the plasma to accelerate. The Lorentz force is also crucial to the operation of most pulsed plasma thrusters.

Pulsed inductive thrusters

Pulsed inductive thrusters (PIT) also use the Lorentz force to generate thrust, but they do not use electrodes, solving the erosion problem. Ionization and electric currents in the plasma are induced by a rapidly varying magnetic field.

Electrodeless plasma thrusters

Electrodeless plasma thrusters use the ponderomotive force which acts on any plasma or charged particle when under the influence of a strong electromagnetic energy density gradient to accelerate plasma electrons and ions in the same direction, thereby operating without a neutralizer.

VASIMR

VASIMR

VASIMR, short for Variable Specific Impulse Magnetoplasma Rocket, uses radio waves to ionize a propellant into a plasma. A magnetic field then accelerates the plasma out of the engine, generating thrust. A 200-megawatt VASIMR engine could reduce the time to travel from Earth to Jupiter or Saturn from six years to fourteen months, and from Earth to Mars from 6 months to 39 days.

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