An overview of the development of HNF and HNF-based propellants

Schoeyer, H.; Korting, P.A.O.G.; Veltmans, W. H. M.; Louwers, J.; Heijden, Antoine van der; Keizers, H.L.J.; Berg, R. van der

doi:10.2514/6.2000-3184

Cited by 12 publications

(17 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Poly (3‐nitratomethyl‐3‐methyloxetane)/HNF propellant has comparable impact sensitivity than non aluminized HTPB/AP propellant but more sensitive than aluminized HTPB/AP propellant. Friction sensitivity of aluminized polyNIMMO/HNF propellant is slightly less than non aluminized HTPB/AP propellant …”

Section: Poly (3‐nitratomethyl‐3‐methyloxetane) (Polynimmo)mentioning

confidence: 99%

Nitrato Functionalized Polymers for High Energy Propellants and Explosives: Recent Advances

Gayathri

Reshmi

2017

Polymers for Advanced Techs

View full text Add to dashboard Cite

Future propellants and explosive research focus on developing compositions with less vulnerability without compromising performance. This has provided impetus for research in the area of high energy materials and compounds free from pollution, for safe handling, high performance, reliability and reproducibility. The energetic oxidizers and energetic binders are being developed in this scenario for use in composite propellants and explosives. In a propellant, the binder holds together the matrix containing solid oxidizer particles and finely divided metal particles. It provides structural integrity and aid the combustion of the propellant. Any new development in this area wherein the binder can contribute to the energetic is of immense importance. This can be achieved by incorporation of energetic groups such as nitrato (−ONO2), azide (−N3) or flurodinitro CF(NO2)2 as side chain or on to the existing polymer backbone. Among these, nitrato functionalized energetic binders can find application in myriad areas like boosters, plastic bonded explosives, gas generators and pyrogen igniters. The present article is a concise review on various types of nitrato binders; their synthesis, properties and their propellant studies. Copyright © 2017 John Wiley & Sons, Ltd.

show abstract

Section: Poly (3‐nitratomethyl‐3‐methyloxetane) (Polynimmo)mentioning

confidence: 99%

Nitrato Functionalized Polymers for High Energy Propellants and Explosives: Recent Advances

Gayathri

Reshmi

2017

Polymers for Advanced Techs

View full text Add to dashboard Cite

show abstract

“…Various GAP/HNF-based propellants have been developed by TNO, NL [106]. These had acceptable mechanical properties, a propellant denoted K-1 which had a maximum stress of 0.69 MPa and a strain of 27% at 20°C.…”

Section: Poly(glycidyl Azide)mentioning

confidence: 99%

“…PolyNIMMO has also been used as a binder of HNF/Al-based propellants [106]. Mixtures of polyNIMMO diols and triols, or triols alone, have both been used.…”

Section: Poly(3-nitratomethyl-3-methyloxetane)mentioning

confidence: 99%

See 1 more Smart Citation

Binder Materials for Green Propellants

Eldsäter

Malmström

2014

Green Energetic Materials

View full text Add to dashboard Cite

“…"Green" means different things to different people; nevertheless, the European Space Agency has a solid definition [3] and the green technologies identified to date include green propulsion, aimed at reducing the toxicity of spacecraft propellants. The most promising high-energy green propellants are based on energetic ionic liquids, such as ammonium dinitramide, hydroxylammonium nitrate, and hydrazinium nitroformate [4,5], that entail high operational temperatures of the exhaust gases. As a consequence, it is necessary to use extremely expensive materials and manufacturing processes for the thrust chamber and, at the same time, the operational life of the catalytic beds is drastically reduced.…”

mentioning

confidence: 99%

Platinum Catalysts Development for 98% Hydrogen Peroxide Decomposition in Pulsed Monopropellant Thrusters

Dolci¹,

Dell’Amico²,

Pasini³

et al. 2015

Journal of Propulsion and Power

View full text Add to dashboard Cite

A number of platinum catalysts for the decomposition of 98% hydrogen peroxide, based on different substrates, geometries, and sizes, have been prepared using different procedures. The catalysts have undergone a set of dedicated tests for screening their catalytic activity and their thermomechanical resistance in order to identify the most efficient and suitable catalyst to be used for a pulsed monopropellant propulsion system. An experimental test campaign on a 20 N monopropellant thruster prototype has been carried out with the aim of assessing the capability of the finally selected new Pt∕α-Al 2 O 3 catalysts of effectively decomposing 98% hydrogen peroxide and the attainable propulsive performance in steady-state conditions for the future assessment of the propulsive performance of the intrinsically unsteady new propulsion concept. The catalysts have been able to decompose up to 1 liter of 98% H 2 O 2 with very good efficiencies (hc > 95% and hΔT ≥ 90%) and without any pellet breakage or catalytic degradation. The thrust profile has been particularly smooth and the experimental specific impulse measured at sea level with the matched conical nozzle has been 130 s, which corresponds to an extrapolated vacuum specific impulse for a high-expansionarea-ratio bell-contoured nozzle higher than 185 s. Nomenclature A = catalytic bed cross-sectional area, which is equal to= theoretical thrust coefficient, which is equal to γ 2∕γ1 γ1∕γ−1 2∕γ−11−p e ∕p C γ−1∕γ p p e −p a ∕p C A e ∕A t fγ; A e ∕A t ; p a ∕p C c = characteristic velocity, which is equal to p C A t ∕m, m∕s c theo = theoretical characteristic velocity, which is equal to which is equal to RT∕γ p γ1∕2 γ1∕2γ−1 , m∕s D = catalytic bed diameter, m D e = nozzle exit diameter, m D t = nozzle throat diameter, m F = thrust, N G = bed load or mass flux, which is equal to m∕A, kg∕s · m 2 g = gravitational acceleration at sea level, m∕s 2 I sp = specific impulse, which is equal to F∕mg, s I sp exp vacuum = vacuum specific impulse extrapolated from the experimental results, s L = catalytic bed length, m m = propellant mass flow rate, kg∕s or g∕s p C = chamber pressure, Pa or bar p CATBEDinlet = inlet catalytic bed pressure, Pa or bar p ENGINEinlet = inlet engine pressure (after the firing valve and before the injector), Pa or bar p TANK = tank pressure, Pa or bar R = gas constant of the exhaust gases, J∕kg · K S BET = specific surface area, m 2 ∕g T ad = adiabatic decomposition temperature, K or°C T amb = ambient temperature, K or°C T C = combustion chamber temperature, K or°C T i = initial temperature, K or°C T TANK = propellant temperature inside the tank, K or°C T 3;4 = temperatures at different stations along the bed, K or°C t max = time to reach the peak temperature, s t 90% = thrust rise time, s α conical = conical half angle, deg γ = specific heat ratio of the exhaust gases Δp CATBED = pressure drop across the catalytic bed, which is equal to p CATBEDinlet −p C , Pa or bar Δp ENGINE = pressure drop across the engine, which is equal to p ENGINEinlet − p C , Pa or ba...

show abstract

An overview of the development of HNF and HNF-based propellants

Cited by 12 publications

References 9 publications

Nitrato Functionalized Polymers for High Energy Propellants and Explosives: Recent Advances

Nitrato Functionalized Polymers for High Energy Propellants and Explosives: Recent Advances

Binder Materials for Green Propellants

Platinum Catalysts Development for 98% Hydrogen Peroxide Decomposition in Pulsed Monopropellant Thrusters

Contact Info

Product

Resources

About