Study on electrical ignition and micro-explosion properties of HAN-based monopropellant droplet

Yu, Yonggang; Li, Ming; Yan-huang, Zhou; Lu, Xin; Yu-zhu, Pan

doi:10.1007/s11708-010-0010-4

Cited by 12 publications

(5 citation statements)

References 13 publications

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“…Recently, a new technique based on electrolysis was successfully demonstrated in the decomposition of HAN-based propellant in different forms, such as high electrical voltage [8], continuous flowing of HAN solution [9], static testing of HAN-based propellant droplet [10]. External parameters that affect the electrolytic decomposition, e.g.…”

Section: Introductionmentioning

confidence: 99%

Calorimetric study on electrolytic decomposition of hydroxylammonium nitrate (HAN) ternary mixtures

et al. 2019

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Electrolytic decomposition of hydroxylammonium nitrate (HAN) is appealing for development of chemical micropropulsion system due to its effectiveness in thermal management. In this paper we present the decomposition characteristics and behaviour of various HAN ternary mixtures prepared according to 0 Oxygen Balance (0 OB). There are multiple stages of decomposition depending on the type of fuels added into the HAN solution. While concentrated HAN solution (73 wt%) has only single stage of decomposition, the saccharides-based HAN ternary mixtures has three stages reaction with increased energy release. The addition of nitrogen-rich compounds has sustained the electrolytic decomposition process into the second stage of reaction, which produced the highest decomposition temperature. The study also reveals a linear relationship between the electrical resistivity of HAN ternary mixture and reaction rate in the first stage of reaction, indicating the presence of Joule heating in the process. The influence of electrical resistivity of the ternary mixture became negligible in the second stage of reaction. This work concludes the importance of combined electrical and thermal energy in the first stage decomposition of HAN ternary mixtures.

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Section: Introductionmentioning

confidence: 99%

Calorimetric study on electrolytic decomposition of hydroxylammonium nitrate (HAN) ternary mixtures

et al. 2019

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“…One conceivable reason may be caused by an electric resistance of SHP163. Although it is not same as SHP163, it is reported that one of HAN based monopropellant LP1846 has non-negligible high electric resistance 17 . Due to non-negligible propellant electric resistance, discharge voltage becomes higher when the power supply works at a constant current mode.…”

Section: B Propellant Ignition Results In the Case Of Argonmentioning

confidence: 98%

Basic Characteristics of Discharge Plasma Ignition System for 1N-class RCS Thruster with Green Monopropellant

Iizuka¹,

Shindo²,

Wada³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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A new ignition system utilizing discharge plasma for reaction control system (RCS) thrusters with green monopropellant is designed and evaluated experimentally in this study. The discharge plasma ignition system laboratory model (DPI-LM) is designed for one of hydroxyl ammonium nitrate (HAN) based monopropellant, SHP163; moreover, the DPI-LM is in substitution for conventional solid catalyst. Objectives of this study are (1) to design and build of DPI-LM and (2) evaluate basic propellant ignition characteristics in terms of successful and stable propellant ignition conditions, power consumption, and fundamental lifetime estimation. In addition, in order to generate discharge plasma prior to propellant ignition, a noble gas is used. Effect of noble gas type, argon and helium, on propellant ignition characteristics are also evaluated. Argon gas shows better propellant ignition with wide ranges of argon and SHP163 mass flow rates. It is considered that the propellant ignition strongly connects to discharge plasma diffusion condition prior to ignition. The power consumption at an argon mass flow rate of 0.075 g/s and a SHP163 mass flow rate of 0.3 g/s is approximately 270 W. The electrode degradation as a function of accumulated experiment time is evaluated as simplified lifetime estimation. The results of the degradation is only 0.1 % in electrode mass at 2000s , and the stable propellant ignition keeps at an accumulated time of 2000 s. Nomenclature I (t) = instantenous discharge current PW = power consumption t p,i = beginning time of the phase t p,f = end time of the phase V (t) = instantenous discharge voltage Δt p = duration of the phase 1 Graduate Student, Department of Aerospace Engineering, tiizuka@astak3.sd.tmu.ac.jp, Student Member.

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“…When the pressure rises, the electrochemical decomposition rate of HAN is accelerated. The micro‐explosion characteristics of HAN [31] in ECSP without C during decomposition and combustion are more obvious, which is the reason for the formation of these holes. The addition of C makes the burning surface of ECSP at 0.1 MPa compact, accompanied by agglomeration of a small amount of combustion products (Figure 4e).…”

Section: Resultsmentioning

confidence: 99%

“…When the voltage is applied to the propellant, the HAN oxidizer begins to electrolysis and ion migrates. The complex reaction process in the propellant includes current density effects, electric power deposition, ohmic heating effects, and electrolytic mechanisms [31, 32]. The electrical response occurs only at an electrode and not throughout the bulk propellant or on any exposed surface whether burning or non‐burning [15].…”

Section: Resultsmentioning

confidence: 99%

Exploring the Influences of Conductive Graphite on Hydroxylammonium Nitrate (HAN)‐Based Electrically Controlled Solid Propellant

Bao

Wang

Zheng³

et al. 2020

Propellants Explo Pyrotec

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The electrically controlled solid propellant (ECSP) has many advantages that are not available with traditional propellants, such as multiple start/stop operations and controllable thrust. In this research, conductive graphite (C) was employed as an additive to hydroxylammonium nitrate (HAN)‐based ECSPs to enhance electrical conductivity and thermal conductivity, and the influences of C on the burning characteristics of ECSPs were investigated by some characterization methods. The addition of 5 % C increases the electrical conductivity and thermal conductivity by 13.2 % and 18.9 %, while reduces the theoretical specific impulse (Isp) and adiabatic flame temperature (Tf) by 7.9 % and 18.4 %. C acting as electric and heat energy transfer media was demonstrated by TG‐DSC. ECSPs containing 1 %, 3 %, and 5 % C reinforce the burning rate by 11.4 %, 25.6 %, 35.9 % and mass loss by 6.9 %, 22.3 %, 47.8 % at 200 V; and enhance the burning rate by 39.2 %, 62.4 %, 104.9 %, and mass loss by 46.7 %, 84.7 %, 200.1 % at 0.6 MPa. This can be explained by the fact that the increase in electrical conductivity promotes the electrochemical decomposition rate of the ionic oxidizer in ECSPs at atmospheric pressure (0.1 MPa) and the rise in thermal conductivity promotes the heat transfer to the unburned zone of the propellant under high pressure (0.2 MPa∼0.6 MPa).

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Study on electrical ignition and micro-explosion properties of HAN-based monopropellant droplet

Cited by 12 publications

References 13 publications

Calorimetric study on electrolytic decomposition of hydroxylammonium nitrate (HAN) ternary mixtures

Calorimetric study on electrolytic decomposition of hydroxylammonium nitrate (HAN) ternary mixtures

Basic Characteristics of Discharge Plasma Ignition System for 1N-class RCS Thruster with Green Monopropellant

Exploring the Influences of Conductive Graphite on Hydroxylammonium Nitrate (HAN)‐Based Electrically Controlled Solid Propellant

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