Similar articles

Abstract: In this study, we aimed to investigate the detonation wave characteristics of a gel propellant with high boron content. A steady-state detonation wave model of a boron-based gel propellant considering the latent heat of phase change was proposed. The detonation wave model was validated through a comparative analysis with shock tube experiments, which revealed that the maximum deviation in the calculated peak detonation pressure was 8% based on various initial pressures. Upon iterative calculations, the eigenvalue detonation velocity of the boron-based gel propellant under default working conditions was obtained as 1831.5 m/s. Subsequently, the refined model was used to study the structure and characteristics of the detonation wave flow field. The effects of incoming flow conditions, fuel parameters, and initial operating state on the detonation wave flow field of the propellant were investigated numerically. The findings revealed that stable and self-sustaining propagation of the detonation wave can be achieved only when its propagation velocity matches the eigenvalue detonation velocity. Note that an increase in initial temperature resulted in elevated gas phase temperature, density, detonation pressure, and particle phase temperature. An increase in boron content within the gel propellant increased the gas phase temperature but decreased the gas phase density and detonation pressure. At the Chapman-Jouguet (CJ) plane, the gas phase temperature and density, along with the particle phase temperature and detonation pressure, reached their peak values when the oxidizer reacted with the propellant in accordance with the stoichiometric ratio.

含硼凝胶推进剂爆震波特性数值模拟研究

[1]ChenW, ZhangMZ, 2011. The current status and future prospects of gel propellants. The 5th National Conference on Chemical Propellant(in Chinese).

[2]DuanL, XiaZX, FengYC, et al., 2023. Effect of carbon dioxide concentration on the combustion characteristics of boron agglomerates in oxygen-containing atmospheres. Journal of Zhejiang University-SCIENCE A, 24(11):949-959.

[3]FanWJ, ZhouJ, LiuSJ, et al., 2021. Effects of the geometrical parameters of the injection nozzle on ethylene-air continuous rotating detonation. Journal of Zhejiang University-SCIENCE A, 22(7):547-563.

[4]FanWJ, LiuWD, PengHY, et al., 2022. Numerical study on ethylene-air continuous rotating detonation in annular combustors with different widths. Journal of Zhejiang University-SCIENCE A, 23(5):388-404.

[5]FoelscheRO, BurtonRL, KrierH, 1999. Boron particle ignition and combustion at 30-150 atm. Combustion and Flame, 117(1-2):32-58.

[6]GlushkovDO, PaushkinaKK, PleshkoAO, et al., 2023. Ignition and combustion behavior of gel fuel particles with metal and non-metal additives. Acta Astronautica, 202:637-652.

[7]HanJX, BaiQD, ZhangSJ, et al., 2022. Experimental study on propagation characteristics of rotating detonation wave with kerosene fuel-rich gas. Defence Technology, 18(8):1498-1512.

[8]HongT, QinCS, LinWZ, 2009. Numerical simulation of detonation in suspended mixed RDX and aluminum dust. Explosion and Shock Waves, 29(5):468-473 (in Chinese).

[9]HuHB, WengCS, 2011. One dimensional numerical calculation for influence of aluminum concentration on multiphase detonation of suspended gasoline/nano-aluminum-powder liquid drops. Journal of Rocket Propulsion, 37(5):47-51 (in Chinese).

[10]HuHB, WengCS, 2016. Transient characteristics for working process of pulse detonation engine with aluminized gelled fuels. Journal of Solid Rocket Technology, 39(4):463-469 (in Chinese).

[11]HuangLY, GongMQ, ZhangJR, et al., 2024. High-energy-density metallized gel propellant by hydrogen-bonded polymer-small molecules for enhanced stability and shear-thinning performance. Acta Astronautica, 214:356-365.

[12]JinYS, XuX, YangQC, et al., 2022. Combustion behavior of hydrocarbon/boron gel-fueled scramjet. AIAA Journal, 60(6):3834-3843.

[13]KingMK, 1972. Boron ignition and combustion in air-augmented rocket afterburners. Combustion Science and Technology, 5(1):155-164.

[14]KüçükosmanR, DeğirmenciH, YontarAA, et al., 2023. Combustion characteristics of gasoline fuel droplets containing boron-based particles. Combustion and Flame, 255:112887.

[15]LeiZD, ChenZW, YangXQ, et al., 2020. Operational mode transition in a rotating detonation engine. Journal of Zhejiang University-SCIENCE A, 21(9):721-733.

[16]LiJL, FanW, YanCJ, et al., 2009. Experimental investigations on detonation initiation in a kerosene-oxygen pulse detonation rocket engine. Combustion Science and Technology, 181(3):417-432.

[17]LiJL, FanW, YanCJ, et al., 2011. Performance enhancement of a pulse detonation rocket engine. Proceedings of the Combustion Institute, 33(2):2243-2254.

[18]LiSC, WilliamsFA, 1991. Ignition and combustion of boron in wet and dry atmospheres. Symposium (International) on Combustion, 23(1):1147-1154.

[19]LiangK, HuangLY, ZhangJR, et al., 2024. Experimental investigation on detonation characteristics of boron-rich gelled propellant in static premixed combustible gases. Acta Astronautica, 220:263-273.

[20]LiangX, WangRL, 2019. Verification and validation of detonation modeling. Defence Technology, 15(3):398-408.

[21]LiuJD, XiaoW, DaiJ, 2024. The influence of supersonic spatial-temporal coupling disturbance on detonation in an expanded chamber. Aerospace Science and Technology, 147:109024.

[22]LiuL, XiaZX, HuangLY, et al., 2020. Numerical investigation of one-dimensional unsteady detonation wave characteristics of magnesium particle-air mixture. Acta Physica Sinica, 69(19):194701 (in Chinese).

[23]LiuWD, PengHY, LiuSJ, et al., 2023. Research progresses of rotating detonation combustion and its application. Acta Aeronautica et Astronautica Sinica, 44(15):528875 (in Chinese).

[24]LuXY, KaplanCR, OranES, 2021. A chemical-diffusive model for simulating detonative combustion with constrained detonation cell sizes. Combustion and Flame, 230:111417.

[25]MengHL, XiaoQ, FengWK, et al., 2022. Air-breathing rotating detonation fueled by liquid kerosene in cavity-based annular combustor. Aerospace Science and Technology, 122:107407.

[26]MiaoSK, ZhouJ, LiuY, et al., 2019. Review of studies on oblique detonation waves in supersonic flows. Journal of Experiments in Fluid Mechanics, 33(1):41-53 (in Chinese).

[27]NachmoniG, NatanB, 2000. Combustion characteristics of gel fuels. Combustion Science and Technology, 156(1):139-157.

[28]PadwalMB, NatanB, MishraDP, 2021. Gel propellants. Progress in Energy and Combustion Science, 83:100885.

[29]PalaszewskiB, JurnsJ, BreisacherK, et al., 2004. Metallized gelled propellants combustion experiments in a pulse detonation engine. The 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.

[30]PangWQ, YetterRA, DelucaLT, et al., 2022. Boron-based composite energetic materials (B-CEMs): preparation, combustion and applications. Progress in Energy and Combustion Science, 93:101038.

[31]Rojas ChavezSB, ChatelainKP, LacosteDA, 2023. Two-dimensional visualization of induction zone in hydrogen detonations. Combustion and Flame, 255:112905.

[32]SalvadoriM, PanchalA, MenonS, 2023. Simulation of liquid droplets combustion in a rotating detonation engine. Proceedings of the Combustion Institute, 39(3):3063-3072.

[33]SchumakerSA, KniselyAM, HokeJL, et al., 2021. Methane–oxygen detonation characteristics at elevated pre-detonation pressures. Proceedings of the Combustion Institute, 38(3):3623-3632.

[34]ShaoYT, LiuM, WangJP, 2010. Numerical investigation of rotating detonation engine propulsive performance. Combustion Science and Technology, 182(11-12):1586-1597.

[35]ShenDW, MaJZ, ShengZH, et al., 2022. Spinning pulsed detonation in rotating detonation engine. Aerospace Science and Technology, 126:107661.

[36]SunHJ, ZhangHB, BaiBF, 2008. Evaporation investigation of single droplet in high temperature fuel gas. Journal of Xi’an Jiaotong University, 42(7):833-837 (in Chinese).

[37]SunZP, HuangY, LuanZY, et al., 2023. Three-dimensional simulation of a rotating detonation engine in ammonia/hydrogen mixtures and oxygen-enriched air. International Journal of Hydrogen Energy, 48(12):4891-4905.

[38]von KampenJ, AlberioF, CiezkiHK, 2007. Spray and combustion characteristics of aluminized gelled fuels with an impinging jet injector. Aerospace Science and Technology, 11(1):77-83.

[39]WangF, WengCS, 2022. Numerical research on two-phase kerosene/air rotating detonation engines. Acta Astronautica, 192:199-209.

[40]WangZG, LiangJH, DingM, et al., 2009. A review on hypersonic airbreathing propulsion system. Advances in Mechanics, 39(6):716-739 (in Chinese).

[41]YangDL, XiaZX, HuangLY, et al., 2018. Exprimental study on the evaporation characteristics of the kerosene gel droplet. Experimental Thermal and Fluid Science, 93:171-177.

[42]YuanJF, LiuJZ, ZhangLQ, et al., 2021. Combustion and agglomeration characteristics of boron particles in boron-containing fuel-rich propellant. Combustion and Flame, 232:111551.

[43]ZhouJH, LiuJZ, ZhangYW, et al., 2015. Ignition and Combustion of Boron. Science Press, Beijing, China(in Chinese).