Effect of voltage and droplet size on electrical ignition characteristics of ADN-based liquid propellant droplet

Li, Lei; Li, Guo-Xiu; Li, Hong‐Meng; Yao, Zhaopu

doi:10.1016/j.ast.2019.105314

Cited by 25 publications

(4 citation statements)

References 29 publications

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“…In the past few decades, traditional hydrazine-based liquid propellants have dominated the space propulsion field [ 1 ]. However, in the long-term use process, many problems such as low specific impulse, flammability and explosion, environmental pollution, biological hazards, expensive launch equipment, and sustainable use have become increasingly prominent [ 2 , 3 , 4 ]. Due to the current global energy shortage and increasingly serious environmental problems, green and high-performance propellants have attracted more and more attention, and at the same time, higher requirements have been placed on the research and development of aerospace propellants [ 5 ].…”

Section: Introductionmentioning

confidence: 99%

“…At present, the ADN-based liquid propellants used in space propulsion are mainly chemical propulsion, and the catalytic decomposition, ignition and combustion of ADN-based liquid propellants have been studied meticulously and extensively [ 12 , 13 , 14 ]. Nevertheless, chemical fuel propulsion has the disadvantages of requiring a catalyst, preheating, adjusting feed pressure, complicated combustion chamber structure and low specific impulse [ 2 , 15 , 16 ]. Traditional electric propulsion systems have drawbacks such as higher operating voltage and too low thrust [ 17 ].…”

Section: Introductionmentioning

confidence: 99%

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Transmissive Mode Laser Micro-Ablation Performance of Ammonium Dinitramide-Based Liquid Propellant for Laser Micro-Thruster

Zheng

Mao

et al. 2023

Micromachines

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The transmissive mode laser micro-ablation performance of near-infrared (NIR) dye-optimized ammonium dinitramide (ADN)-based liquid propellant was investigated in laser plasma propulsion using a pulse YAG laser with 5 ns pulse width and 1064 nm wavelength. Miniature fiber optic near-infrared spectrometer, differential scanning calorimeter (DSC) and high-speed camera were used to study laser energy deposition, thermal analysis of ADN-based liquid propellants and the flow field evolution process, respectively. Experimental results indicate that two important factors, laser energy deposition efficiency and heat release from energetic liquid propellants, obviously affect the ablation performance. The results showed that the best ablation effect of 0.4 mL ADN solution dissolved in 0.6 mL dye solution (40%-AAD) liquid propellant was obtained with the ADN liquid propellant content increasing in the combustion chamber. Furthermore, adding 2% ammonium perchlorate (AP) solid powder gave rise to variations in the ablation volume and energetic properties of propellants, which enhanced the propellant enthalpy variable and burn rate. Based on the AP optimized laser ablation, the optimal single-pulse impulse (I)~9.8 μN·s, specific impulse (Isp)~234.9 s, impulse coupling coefficient (Cm)~62.43 dyne/W and energy factor (η)~71.2% were obtained in 200 µm scale combustion chamber. This work would enable further improvements in the small volume and high integration of liquid propellant laser micro-thruster.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Transmissive Mode Laser Micro-Ablation Performance of Ammonium Dinitramide-Based Liquid Propellant for Laser Micro-Thruster

Zheng

Mao

et al. 2023

Micromachines

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“…Liquid propellant is a substance that provides energy and working medium for a propulsion system, which is widely used in a variety of rockets, satellites and weapon systems. Liquid propellants have advantages of large specific impulse, high combustion heat, adjusting thrust easily, being capable of multiple ignitions, and so forth [1][2][3]. Anhydrous hydrazine (N 2 H 4 ) is one of the most commonly used storable liquid propellants, which is also an important intermediate in the fields of medicine, chemical industry, biology and pesticide for its strong reducibility and toxicity [4,5].…”

Section: Introductionmentioning

confidence: 99%

Comparative Study on the Damage Effects in the Deflagration Process of Typical Liquid Propellants

Sang

et al. 2022

Propellants Explo Pyrotec

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To study the damage effects caused by accidental deflagration of liquid propellants during production, storage, transportation and use, the information of the deflagration processes and the shock wave hazards of three typical liquid propellants under external flame stimulation were obtained by a high-speed camera and a shock wave pressure acquisition system. Additionally, in the same situation, the highest temperature of the surface fireball and the law of fireball of the thermal radiation were also studied by an infrared thermal imager and heat flux test system. High-speed video results showed that the fireball of DT-3 developed most violently of the three liquid propellants; anhydrous hydrazine took the second place and metallized gelled MMH was the weakest. The average TNT equivalents of 18 kg anhydrous hydrazine, 18 kg DT-3, 120 kg anhy-drous hydrazine and 120 kg DT-3 were 0.724, 0.629, 0.000375 and 0.0293 respectively. The peak values of thermal radiation flux were in the order of DT-3 > anhydrous hydrazine > metallized gelled methylhydrazine. The corresponding death radius in the accident was supposed to be 20-30 m. Experimental results indicated that package design pressure of liquid propellant had a significant effect on the intensity of the reaction response to the action of flame stimulation. Within a certain range, the package design pressure of liquid propellant should be appropriately reduced to improve its security in storage and use. The study provided a theoretical guidance for the explosion protection of liquid propellant in case of accidental deflagration.

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“…Notably, an electrical ignition device for ADN droplets has been developed successfully for combustion. Research has investigated the impact of on-load voltage on the combustion characteristics of ADN-based liquid propellants [17,18]. It was found that the evaporation, decomposition, and combustion durations differed from those of other liquid droplets [19][20][21].…”

mentioning

confidence: 99%

Thermal Decomposition of Ammonium Dinitramide (ADN) as Green Energy Source for Space Propulsion

Harimech,

Toshtay,

Atamanov

et al. 2023

Aerospace

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The thermal decomposition of an ammonium dinitramide-based energetic compound was conducted for the first time using a dispersive inductively coupled plasma mass spectrometer, DTA-TG analysis, and pyrolysis at a constant temperature. A liquid droplet was injected over synthesized CuO catalytic particles deposited on lanthanum oxide-doped alumina. The thermal behavior of the ADN liquid monopropellant revealed that decomposition in the presence of catalytic particles occurs in two distinct steps, with the majority of ejected gases being detected in real-time analysis using the DIP-MS technique. At a temperature of 280 °C, pyrolysis confirmed the catalytic decomposition behavior of ADN, which occurred in two distinct steps.

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Effect of voltage and droplet size on electrical ignition characteristics of ADN-based liquid propellant droplet

Cited by 25 publications

References 29 publications

Transmissive Mode Laser Micro-Ablation Performance of Ammonium Dinitramide-Based Liquid Propellant for Laser Micro-Thruster

Transmissive Mode Laser Micro-Ablation Performance of Ammonium Dinitramide-Based Liquid Propellant for Laser Micro-Thruster

Comparative Study on the Damage Effects in the Deflagration Process of Typical Liquid Propellants

Thermal Decomposition of Ammonium Dinitramide (ADN) as Green Energy Source for Space Propulsion

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