Monomethylhydrazine Research Articles

Design and assessment of an advanced renewable energy system with hydrogen and monomethylhydrazine production for space shuttles

A new renewable energy-driven advanced plant is designed and developed to produce multiple useful outputs, namely electricity, heat, cooling, hydrogen, and monomethylhydrazine (as space shuttle fuel) using solar and wind energies locally available. A specific location needed for this kind of unique work is identified as the Kennedy Space Center (KSC), which is known as located on Merritt Island, in the state of Florida (USA). It is also one of the National Aeronautics and Space Administration's (NASA) ten field centers. Since December 1968, KSC has been NASA's primary launch center of American spaceflight, research, and technology. This paper presents a comprehensive analysis of the subsystems that constitute the newly proposed system potentially for KSC and highlights their complex relationships and synergies. Leveraging renewable energy sources, such as concentrated solar power (CSP) and wind energy, coupled with the subsystem uniquely, such as the regenerative Rankine cycle, multi-stage flash (MSF) desalination unit, hydrogen production process, and Li–Br absorption chiller, the KSC's system maximizes energy conversion efficiency while minimizing environmental impact. Noteworthy outcomes include daily water production of 177.63 kg/s and hydrogen production of 169.61 kg/day, alongside annual energy contributions of 212,692,688 kWh for CSP and 66,158,552 kWh for wind turbines. More than that, it produces 23.04 kg/s MMH as fuel. Additionally, the overall energy and exergy efficiencies of the system are 30.6% and 33% respectively. Despite challenges, such as low efficiencies in certain subsystems, like mono methyl hydrazine (MMH) production, ongoing research and development efforts aim to optimize processes and enhance sustainability.

Optimal Liquid Engine Architecture by Performance-Cooling Tradeoff Analysis

We perform physics-based theoretical analyses on the tradeoff between the overall performance of specific impulse and the thermal protection ability of a coolant liquid film to identify the optimal configuration of a liquid rocket engine. A bipropellant thruster is set as the target, which uses a hypergolic propellant mixture of nitrogen tetroxide as the oxidant and monomethyl hydrazine as the fuel. By considering the practical nonuniform distribution of the local mixture ratio produced in the thrust chamber, the maximum specific impulse is achieved when the fuel and oxidizer spray widths become identical, allowing for the specification of the diameter of the impinging-type injector. The heat balance between the convective heat transfer from the combustion gas and the latent heat of the three-dimensionally wavy liquid film provides the optimal diameter of the combustion chamber. The longest liquid film is found to be achieved when half of the initial film is entrained by the fast gas, correspondingly mitigating the heat transfer area due to the liquid film waviness. We successfully demonstrate the optimal architecture of the liquid engine based on the tradeoff, in which an improvement of specific impulse by 1 s shortens the film length by 2 mm.

Hydrazine and its Derivatives: Role on Nitrogen Dioxide Hydrolysis and Ensuing Nucleation in the Atmosphere

AbstractHydrazine (HD) and mono‐methyl hydrazine (MMH), as the compositions of rocket fuels and corrosion inhibitor, have a significant impact on the atmospheric environment. The effects of them on the reaction between NO2 and H2O were investigated theoretically from mechanism and kinetics, and it is expected that they can promote the hydrolysis of NO2 due to their lower free energy barriers. For the subsequent reaction HNO3+HONO+HD/MMH, acid base complex and zwitterionic structure were produced through isomerization. When one or two water molecules were involved in the subsequent reaction, only zwitterionic structure can be found with the lower free energy barrier, and the products were more stable than those without water molecules. To study the atmospheric behavior of HD/MMH, the structures, thermodynamics, interaction forces and temperature dependence of the clusters, which were consisted with HNO3 and HONO with the base molecules including ammonia, amine and amide, were further calculated, and the results show that the hydrogen bond is the main interaction in the clusters. The global minima remained fixed when the temperature increases from 200 K to 325 K. The forming reactions of the clusters were spontaneous, suggesting that ammonia, amine and amide can promote the nucleation of HNO3 and HONO molecules.

Experimental research on the detonation behavior in annular combustors utilizing liquid hypergolic propellants

The development of rotating detonation engine utilizing hypergolic propellants is necessary for practical application of detonation-based rocket engines, but this liquid-liquid rotating detonation has been rarely researched due to its difficulty of well atomization and mixing in very short time. This study aims to experimentally investigate the propagation characteristics of rotating detonations using non-premixed hypergolic propellants in annular combustors. Here the monomethyl hydrazine (MMH) and nitrogen tetroxide (NTO) have been used as oxidizer and fuel, respectively. Twenty-four unlike impinging elements have been used for injection and mixing of liquid propellants. The orifice diameter is 0.4 mm for oxidizer and 0.3 mm for fuel. Three typical combustion modes such as deflagration mode, one-wave rotating detonation mode and two-wave collision mode have been captured by dynamic pressure transducers and the high-speed camera. The influence of many factors, such as mass flow rate, mixing ratio, annular combustor width and chamber throat, on rotating detonation behaviors have been investigated. The propagation velocity of rotating detonations is around 1328 m/s∼1405 m/s, including one-wave rotating detonation mode and two-wave collision mode. When the mass flow rate and mixing ratio is not appropriate, the hypergolic combustion becomes obviously unstable and combustion modes vary very quickly, especially at the start-up stage. The chamber throat plays a negative role on rotating detonation which suppresses the detonation propagation and can lead to detonation fail. Besides, the wider annular combustor width is beneficial for rotating detonation propagating, which can eliminate the negative influence of the chamber throat on the detonation propagation. In addition, increasing mass flow rate would lead to higher injection velocity and thus better impinging injection, atomization and mixing, which is positive for increasing the stable operation range of mixing ratio for rotating detonations.

Hydrogen Based Compounds as Energetic Catalysts for Liquid Rocket Engines: Implications and Applications

In the current scenario of space propulsion, liquid propellants have significantly proved useful in the upper stage rocket engines. Over the past couple decades, the world had inclined positively towards cryogenic fuel(s) viz., liquid oxygen and liquid hydrogen due to their high specific impulse. A higher specific impulse implies lower duration to achieve design cruise velocity for a given rocket initial and instantaneous mass. Liquid hydrogen and liquid oxygen as fuel and oxidizer can generate one of the highest enthalpy release in combustion, producing a specific impulse of up to 450 seconds at an effective exhaust velocity of 4.4 kilometres per second. Whereas, selected disadvantages are encountered in the form of storage and production. This indicates overdependence on cryogenic propellants and has necessitated the active research effort for better alternatives. As an interesting alternative, the combination of Dinitrogen Tetroxide (N2O4) and Monomethyl Hydrazine (MMH) have been used for many space applications owing to an extreme storage stability and hypergolic nature. Present study aims to express the effect of hydrogen-based compounds on the rocket performance. Four distinctive compounds from two groups of hydrogen-based compounds are tested with the varying oxidizer and fuel proportions to obtain a new, cost-effective and user-friendly composition that can be prepared at room temperature. The investigation attempt and explains the effect of hydrogen based energetic propellants using N2O4 and MMH as the base composition for upper stage performance. The work is motivated by the need of efficient space operations with attractive propulsive alternatives to minimize over-dependence on cryogenics, which will ultimately result in cost effectiveness. Various energetic materials were tested with the base composition by using standard NASA-CEA complex chemical equilibrium model. The performance was evaluated in terms of variation in specific impulse and characteristic velocity both of which are significant parameters. To, validate the practical utility, the role of chamber pressure, supersonic area ratio and optimal Oxidizer to fuel ratio (O/F) was determined. The work led to two interesting findings, a composition of beryllium hydride with base composition for high performance of rockets and the negative impact of hydrogen on liquid propellants.

Catalyst Free Single Step Specific Determination of Hydrazine in UH 25 blend and Determination of Propellant Grade UH 25 blend Using Thiophenes with Active Carbonyl Groups

AbstractHydrazine and its derivatives such as monomethyl hydrazine (MMH), unsymmetrical dimethyl hydrazine (UDMH), and UH25 (a blend of 75 % UDMH and 25 % hydrazine hydrate by w/w) namely hydrazines are used as fuels (in liquid form) for rocket stages and satellites. They are hypergolic and well‐known toxic compounds. Workplace atmospheres involving vapours / liquid forms of these hydrazines need to be routinely monitored and screened. Simple, economical, and rapid kinetic spectrophotometric techniques are developed to meet the requirements by using thiophene‐3‐carboxaldehyde and 3‐butenone (E)‐1,1,1‐trifluoro‐4‐(3‐thienyl) (CF3enone) and compared. Classical −CHO based technique is applied for UH25 blend (in aqueous medium) in the presence of an acid catalyst. CF3enone based technique is used to determine hydrazine (Hz) in UH25 (in organic medium) selectively at levels as low as 0.05 mM without any catalyst. Variables such as temperature and concentration are optimized to determine UH25 in the concentration range of 0.5 mM to 0.1 M for thiophene‐3‐carboxaldehyde and to determine Hz of UH25 blend in the concentration range of 0.1 mM to 0.6 mM for CF3enone. Minimum detectable limits are found for UH25 and Hz of UH25 blend in the respective studies. GC‐MS study is also carried out to meet the unequivocal identification requirement. Initial rate and fixed time methods are adopted as calibration procedures. Orders of the reactions are found in both studies. Both techniques are simple and rapid after the chemisorption process with derivatizing agents in which pre‐treatment, pre‐concentration, and extraction steps are not involved. Advantages of CF3enone based technique over aldehyde‐based classical technique are 1) requirement of the minimum concentration of derivatizing agent 2) no catalyst 3) selectivity and specificity towards hydrazine in UH25 blend 4) shortened analysis time 5) linear dynamic range at very low concentrations of UH25.

Propellant Off-Gassing and Implications for Triage and Rescue.

INTRODUCTION: Hypergolic propellants can be released in large amounts during space launch contingencies. Whether propellant-contaminated suit fabric poses a significant risk to rescue crews, due to off-gassing, has not been explored in detail. In this study, we addressed this issue experimentally, exposing space suit fabric to propellants (dinitrogen tetroxide [N₂O₄] and monomethyl hydrazine [MMH]).METHODS: The NASA Space Shuttle Program Advanced Crew Escape System II (ACES II) is similar to the NASA Orion Crew Survival System (OCSS) and was utilized here. Suit fabric was placed and sealed into permeation cells. Fabric exterior surface was exposed to constant concentrated hypergolics, simulating permeation and leakage. Fabric was rinsed, and permeation and off-gassing kinetics were measured. Experimental parameters were selected, simulating suited flight crewmembers during an evacuation transport without cabin air flow.RESULTS: The fabric allows for immediate permeation of liquid or vaporized MMH and N₂O₄. NO₂ off-gassing never exceeded the AEGL-1 8-h level (acute exposure guideline level). In contrast, MMH off-gassing levels culminated in peak levels, approaching AEGL-2 10-min levels, paralleling the drying process of the fabric layers. DISCUSSION: Our findings demonstrate that MMH off-gassing is promoted by the drying of suit material in a delayed fashion, resulting in MMH concentrations having the potential for adverse health effects for flight and rescue crews. This indicates that shorter decontamination times could be implemented, provided that suit material is either kept moist to prevent off-gassing or removed prior to medical evacuation. Additional studies using OCSS or commercial crew suits might be needed in the future.Schwertz H, Roth LA, Woodard D. Propellant off-gassing and implications for triage and rescue. Aerosp Med Hum Perform. 2020; 91(12):956961.

Numerical Simulation of Ignition Process for the Monomethyl Hydrazine–Nitrogen Tetroxide Thrusters

The numerical simulation of the ignition process of the monomethyl hydrazine–nitrogen tetroxide attitude-control thrusters is difficult because of the complex hypergolic gas–liquid chemical reaction between the propellants. To calculate the thruster ignition delay accurately, a 36-step gas-phase chemical kinetics model and a one-step finite-rate liquid-phase hypergolic reaction are proposed. These chemical mechanisms are integrated into the Euler–Lagrange-based transient spray combustion simulation platform. The calculated ignition pressure curve of a 2 kN thruster coincides well with that from the experiment. The numerical and experimental ignition delays are 2.4 and 3.1 ms, respectively. A parameter study shows that the liquid-phase reaction at the propellant impingement points consumes 22–44% propellant and provides energy to heat the gas mixtures, which is essential for a successful gas-phase ignition. The lower limit of ignition delay was estimated as 1.5 ms under design restrictions for most thrusters.

Characterization of the Hypergolic Ignition Delay of Ammonia Borane

Hypergolic hybrid motors have the potential to improve the safety, reliability, and versatility of rocket systems. They may also serve as a viable replacement for highly toxic liquid fuels (for example, hydrazine, monomethyl hydrazine, etcetera) conventionally used in hypergolic systems. Ammonia borane (AB)-based fuels are relatively nontoxic hydrogen-dense solids that have good theoretical performance. AB has also been found to be highly hypergolic with white fuming nitric acid (WFNA), potentially enabling it to replace existing toxic hypergolic fuels. In this work, hypergolic ignition delay tests were performed on AB synthesized with a novel water-promoted scalable process to characterize its performance as a hypergolic fuel. Typical ignition delays with WFNA were found here to be approximately 2–10 ms. Ignition delay tests performed with AB powder sieved into different particle size ranges indicated a particle size dependency for the ignition delay, with the finer AB particles () igniting after shorter delays. AB was successfully incorporated into Sylgard®-184, which is a silicone elastomer binder, and ignition delay tests were performed on high solids loading (80%) Sylgard-184-AB pellets. Mean ignition delays for the Sylgard-184-AB fuel pellets tested were less than 50 ms, which may make the formulation viable for use in hypergolic hybrid motors.

Specific Impulse and Ignition Delay Time Assessment for DMAZ with Liquid Oxidizers for an Upper Stage Rocket Engine

2-Dimethyl amino ethyl azide (DMAZ) has attracted much attention as a suitable liquid fuel replacement for monomethyl hydrazine (MMH) and unsymmetrical dimethyl hydrazine (UDMH) in propellant systems because, in contrast to these fuels, it is noncarcinogen. In this research, performance, and ignition delay time of DMAZ were studied with common liquid oxidizers such as inhibited red fuming nitric acid (IRFNA), dinitrogen tetroxide (N2O4), White Fuming Nitric Acid (WFNA). Calculation results from rocket propulsion analysis (RPA) software showed that combustion of DMAZ and N2O4yielded highest Isp (352 s) compared to the other mentioned oxidizers. Moreover, DMAZ-N2O4 gave the highest density specific impulse (457.6­ s) at an optimum oxidizer-to-fuel ratio. Open cup tests were also performed to assess the ignition behavior of the DMAZ-N2O4 bipropellant and indicated that it is hypergolic (68 ms). Therefore, it seems that the DMAZ-N2O4 bipropellant is suitable for upper stage space systems.

Synthesis and Ignition Properties Research of 1,5-Diazabicyclo[3.1.0]Hexane Type Compounds as Potential Green Hypergolic Propellants

1,5-Diazabicyclo[3.1.0]hexane type compounds (DABHCs) were found as promising liquid hypergolic compounds. The synthesis process and purification of DABHCs, 1,5-diazabicyclo[3.1.0]hexane (DABH), 6-methyl-1,5-diazabicyclo[3.1.0]hexane (MDABH), 6-ethyl-1,5-diazabicyclo[3.1.0]hexane (EDABH), and 6,6-dimethyl-1,5-diazabicyclo[3.1.0]hexane (DDABH) were optimized. The densities of DABHCs were over 1.0 g/mL, and the viscosities of DABHCs were about 2.40–2.63 mPa·s. The boiling points of DABHCs exhibited that they were less volatile, and the freezing points of DABHCs varied considerably for different alkylation. The LD50 predicted values of DABHCs were within 1605.62–4865.43 mg/kg, which demonstrated that DABHCs were grade IV, slightly poisonous, or grade V, nontoxic, compounds according to the Globally Harmonized System of Classification and Labeling of Chemicals (GHS). In addition, the heats of formation of DABHCs were calculated as 129.2–276.2 kJ/mol, higher than those of monomethyl hydrazine, unsymmetrical di...

Thermal Decomposition Research on 1,5‐Diazabicyclo[3.1.0] Hexane (DABH) as a Potential Low‐toxic Liquid Hypergolic Propellant

Abstract1,5‐Diazabicyclo[3.1.0] hexane (DABH) was found a potential hypergolic liquid propellant. The physical and energetic properties of DABH, 2‐(dimethylamino) ethyl azide (DMAZ), and monomethyl hydrazine (MMH) were compared. The ignition delay time of DABH with nitrogen tetroxide was 1 ms, which was shorter than DMAZ and similar with MMH. The toxicology experiment showed that half lethal dose (LD50) of DABH was 621.0 mg kg−1, which suggested that DABH was promising to be used as low‐toxic liquid propellant. Thermal decomposition experiments showed that the apparent activation energy (E) was about 66.3 kJ mol−1. The thermal decomposition calculated results from Madhusudanan‐Krishnan‐Ninan integration, Satava‐Sestak integration and Achar differential methods were compared and the pre‐exponential factor were obtained.

Ionic Liquid and Biofuel Blend: A Low–cost and High Performance Hypergolic Fuel for Propulsion Application

AbstractHypergolic fuel has unique importance in missiles and satellite launch vehicles. Hydrazine and its derivatives (Monomethyl hydrazine, MMH and Unsymmetrical Dimethyl Hydrazine, UDMH) are the continuous choices of fuel in bipropellant though it is carcinogenic and toxic. Development of new, green and cost‐effective fuel blends based on trust‐worthy, ionic liquid and biofuel in different volume proportion have been reported. The blends exhibit reasonably good stability (chemical and thermal), low viscosity (η < 15 mPa⋅s), high density (ρ > 1 g/cm3), low ignition delay and high performance in comparison with UDMH ‐ a proven liquid fuel presently being used as promising fuels for liquid rocket application. The reported blends appear to be a technologically promising, eco‐friendly and affordable fuel blend to replace currently used liquid toxic fuels.

Cryogenic propulsion for the Titan Orbiter Polar Surveyor (TOPS) mission

Liquid hydrogen (LH2) and liquid oxygen (LO2) cryogenic propellants can dramatically enhance NASA’s ability to explore the solar system due to their superior specific impulse (Isp) capability. Although these cryogenic propellants can be challenging to manage and store, they allow significant mass advantages over traditional hypergolic propulsion systems and are therefore enabling for many planetary science missions. New cryogenic storage techniques such as subcooling and the use of advanced insulation and low thermal conductivity support structures will allow for the long term storage and use of cryogenic propellants for solar system exploration and hence allow NASA to deliver more payloads to targets of interest, launch on smaller and less expensive launch vehicles, or both. These new cryogenic storage technologies were implemented in a design study for the Titan Orbiter Polar Surveyor (TOPS) mission, with LH2 and LO2 as propellants, and the resulting spacecraft design was able to achieve a 43% launch mass reduction over a TOPS mission, that utilized a traditional hypergolic propulsion system with mono-methyl hydrazine (MMH) and nitrogen tetroxide (NTO) propellants. This paper describes the cryogenic propellant storage design for the TOPS mission and demonstrates how these cryogenic propellants are stored passively for a decade-long Titan mission that requires the cryogenics propellants to be stored for 8.5years.

An ab initio Based Structure Property Relationship for Prediction of Ignition Delay of Hypergolic Ionic Liquids

AbstractCurrently, monomethyl hydrazine is the most widely used hypergolic rocket fuel. However, due to its high vapor toxicity, there is a need to develop low‐toxicity hypergolic fuels. Ionic liquids are one such potential category of fuels, since they are consistently characterized by ultra‐low vapor pressures, but designing ionic liquid propellants with ignition delay times that are comparable to that of monomethyl hydrazine is a challenge. This is because a fundamental understanding of the hypergolic nature of ionic liquids is far from clear. Quantitative structure property relationship (QSPR) represents a simplified design approach for quantitatively predicting the ignition delay times based on linear correlations using a set of descriptors, which, in this work, define electrostatics, hydrogen bonding, and other structural features of the ionic liquids. Experimental ignition delay times for a set of 41 ionic liquids were collected for QSPR development. Experimental measurements of the ignition delay times were then correlated to theoretical descriptors determined from quantum mechanical calculations. A number of multi‐descriptor linear equations were analyzed by regression of the ignition delay data, showing reasonable success. The ignition delay values were observed to spread over a wide range, in large part due to the presence of oxygen in the fuel molecule. The training data was thus split into two sets and refitted to a set of linear equations, showing a systematic improvement in the correlation coefficients. The success of the present QSPR results is encouraging, which should motivate further efforts to enlarge the training set to include experimentally measured properties of ionic liquids for developing highly predictive capabilities.

Pervaporation performance of PPO membranes in dehydration of highly hazardous mmh and udmh liquid propellants

Polyphenylene oxide (PPO) membranes synthesized from 2,6-dimethyl phenol monomer were subjected to pervaporation-based dehydration of the highly hazardous and hypergolic monomethyl hydrazine (MMH) and unsymmetrical dimethyl hydrazine (UDMH) liquid propellants. Membranes were characterized by TGA, DSC and SEM to study the effect of temperature besides morphologies of surface and cross-section of the films, respectively. Molecular dynamics (MD) simulation was used to study the diffusion behavior of solutions within the membrane. CFD method was employed to solve the governing mass transfer equations by considering the flux coupling. The modeling results were highlighted by the experimental data and were in good agreement. High separation factors (35–70) and reasonable water fluxes (0.1–0.2kg/m2h) were observed for separation of the aqueous azeotropes of MMH (35wt%) and UDMH (20wt%) and their further enrichment to >90% purity. Effect of feed composition, membrane thickness and permeate pressure on separation performance of PPO membranes were investigated to determine optimum operating conditions.

Performance Evaluation of Liquid Fuel 2-Dimethyl Amino Ethyl Azide (DMAZ) with Liquid Oxidizers

2-Dimethyl amino ethyl azide (DMAZ) has attracted much attention as a suitable liquid fuel replacement for monomethyl hydrazine (MMH) and unsymmetrical dimethyl hydrazine (UDMH) in propellant systems because, in contrast to these fuels, it is nontoxic. In this article, performance and ignition delay of DMAZ were studied with common liquid oxidizers including inhibited red fuming nitric acid (IRFNA), anhydrous nitric acid, dinitrogen tetroxide (N2O4), hydrogen peroxide (H2O2), liquid oxygen (LOX), and mixed oxides of nitrogen (MON). Results showed that combustion of DMAZ and LOX provides the highest specific impulse (305.8 s) compared to the other mentioned oxidizers. Moreover, DMAZ and H2O2 gave the highest density specific impulse (360.2 s) at an optimum oxidizer-to-fuel ratio due to the higher density of hydrogen peroxide. Furthermore, a mixture of DMAZ and N2O4 had the minimum ignition delay time (68 ms). Therefore, it seems that the DMAZ-N2O4 propellant combination is suitable for space systems.

Hypergolic Propellant Ignition Phenomenon Associated with Two-Phase Oxidizer Flow Injection

During pulse-mode operation of a bipropellant engine that uses mixed oxides of nitrogen and monomethyl hydrazine as a propellant, a titanium alloy injector with an unlike-doublet impinging stream absorbs the heat from the injector face, which is heated to a high temperature during combustion. When the injector’s temperature exceeds the boiling point of the oxidizer under several operating conditions, evaporation will occur at the initial inflow of each pulse. This evaporation phenomenon causes an unsteady two-phase flow that affects ignition and combustion phenomena. In this paper, this abnormal ignition and combustion phenomenon associated with the two-phase flow is investigated through experiments with a single-element injector. Data analysis on the impinging stream instability and the ignition phenomenon reveals that the unsteady oxidizer jet caused by evaporation may act as a trigger for high-frequency instability.

Molecular Orbital Based Design Guideline for Hypergolic Ionic Liquids

AbstractCurrently, monomethyl hydrazine is the most widely used hypergolic rocket fuel. Due to its high toxic vapor, there is a thrust towards developing low‐toxic hypergolic fuels. Ultra‐low vapor pressure ionic liquids are one such potential category of fuels. However, designing ionic liquid with ignition delay comparable to monomethyl hydrazine is a challenge, because fundamental understanding of the hypergolic nature of ionic liquids is far from clear. This work used the computed energy gap values between the highest occupied molecular orbitals (HOMO) of the anions for a series of ionic liquids and the lowest occupied molecular orbital (LUMO) of HNO3, and variation in the computed relative heats of formation, ΔHf, of these anions to develop correlations to predict hypergol activity between an ionic liquid fuel and nitric acid as the oxidizer. The observed trends in HOMOLUMO energy gap and ΔHf values can be used successfully to verify not only hypergolicity of known systems but also the lack of this phenomenon in OH− and BF4− based ionic liquids. It was shown that through suitable substitution of electron withdrawing or electron donating groups in the anion, the energy gap and the ΔHf values could be tailored into an optimal range that would have a high probability for the new system to exhibit hypergolic reactivity. To validate our method, we suggest herein new ionic liquid structures for synthesis and experimental screening.

Identification of novel cyanobacterial compounds for oral disease through in vitro and insilico approach

In this research, we have conducted docking study to screen bioactive compounds from Microcystis aeruginosa and Phormidium corium. Among the two blue-green algal species were analyzed for chemical nature of bioactive substances using TLC and GC-MS methods. The antimicrobial compounds identified were phenolics, alkaloids, steroids. In the present study as reported that M. aeruginosa curde extract contained the bioactive compound Microginins, while Cyalobolide B was detected from P. corium. The phytochemical analysis of M. aeruginosa (Microginins), provided ethaneloic acid, Octanal, 3,7,11-Trimethyl-1,6,10-dodecatrien-3-ol (nerolidal), Monomethyl hydrazine and formic acid. The cumulative effect of these phytochemical provided more effective antimicrobial compound in inhibiting microbial growth. The phytochemical analysis of P. corium (Cyalobolide B) exhibited Ethaneloic acid, Dihydrodiplodialide, 3, 7, 11-Trimethyl-1, 6, 10-dodecatrien-3-ol (nerolidal), 1-Dodecanol, 1-Hexadecanol (CAS) and nanonic acid. These compounds together exhibited more effective antimicrobial substance in inhibiting microbial growth. Which members of a community interact with themselves as well as with different host structures and components of Candida albicans and Streptococcus mutans. The pathogenesis of this dental infection is a multi factorial process that results in a serious degenerative disease of the Oral candidiasis. In the present study SAP (secreted aspartyl proteinases in virulence and pathogenesis) is taken as a case study molecule to understand high reactive responses of various drugs administered for the oral candidiasis. The drugs are being compared with the SAP from C. albicans and SpaP (cell surface antigen SpaP gene) from S. mutans. The SAP and SpaP interacted with formic acid, nerolidal, octanol and nonanoic acid using docking methods. The exponentially increasing speed of computational methods makes a more extensive use in the early stages of drug discovery attractive if sufficient accuracy can be achieved.