Experimental study on thermal ignition and combustion of droplet of ammonium dinitramide based liquid propellant in different oxidizing gas atmospheres

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

doi:10.1016/j.actaastro.2019.12.030

Cited by 18 publications

(11 citation statements)

References 20 publications

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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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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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“…Ammonium diamide (ADN)-based liquid propellant is a new type of highperformance, low-toxicity green monopropellant, which, in recent years, has received extensive attention in the military and aerospace fields, representing a new research direction and development trend of space propulsion technology with good application prospects. 1 ADN-based liquid thrusters, which are currently used on satellites, mostly use the catalytic decomposition method to ignite the ADN-based liquid propellant. 2−4 Some scholars also try to use the emerging thermal ignition.…”

Section: Introductionmentioning

confidence: 99%

“…2−4 Some scholars also try to use the emerging thermal ignition. 1,5 The limitations related to the ignition method hinder the development of the green ADN-based propellants in the aerospace field; thus, it is urgent to find a reliable and stable ignition method. In recent years, plasma-assisted ignition has developed rapidly as a new combustion technology in the aeroengine field, and its main principle is to promote auxiliary fuel ignition through plasma discharge.…”

Section: Introductionmentioning

confidence: 99%

“…To this end, the development of pollution-free, recyclable, and green propellants has important scientific significance and application value. Ammonium diamide (ADN)-based liquid propellant is a new type of high-performance, low-toxicity green monopropellant, which, in recent years, has received extensive attention in the military and aerospace fields, representing a new research direction and development trend of space propulsion technology with good application prospects …”

Section: Introductionmentioning

confidence: 99%

“…ADN-based liquid thrusters, which are currently used on satellites, mostly use the catalytic decomposition method to ignite the ADN-based liquid propellant. − Some scholars also try to use the emerging thermal ignition. , The limitations related to the ignition method hinder the development of the green ADN-based propellants in the aerospace field; thus, it is urgent to find a reliable and stable ignition method. In recent years, plasma-assisted ignition has developed rapidly as a new combustion technology in the aeroengine field, and its main principle is to promote auxiliary fuel ignition through plasma discharge. − Common plasma discharges include filamentary discharge, corona discharge, streamer discharge, microwave discharge, surface discharge, and nanosecond pulsed repetitive discharge .…”

Section: Introductionmentioning

confidence: 99%

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Experimental Study on Microwave-Assisted Ignition and Combustion Characteristics of ADN-Based Liquid Propellant

Hou

Liu³

et al. 2021

ACS Omega

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Microwave-assisted ignition is a new ignition method, which has the advantages of reliable ignition and high ignition energy and requires no preheating. In this study, experimental methods were used to study the microwave-assisted ignition and combustion characteristics of ADN-based liquid propellant, and the effects of microwave power and propellant flow rate on combustion flame structure, spectral emission characteristics, and flame temperature were investigated. In the experiment, a microwave-assisted ignition experimental device was established first. The ADN-based liquid propellant was injected into the microwave high-energy region from the bottom of the resonator through a hollow straight tube with an inner diameter of 1 mm, and the gas was introduced in a coaxial manner. The research results demonstrated that when the microwave power increased from 1000 to 2000 W, the flame height increased from 11.12 to 17.32 mm; the free radical intensity of C2*, NH2, and HNO* increased significantly; the flame temperature increased by about 28.9%. The increase in microwave power is helpful to the generation of intermediate products and the combustion performance of propellant is better. When the propellant flow rate was increased from 25 to 45 mL/min, it was found that the spray combustion effect was the best when the propellant flow rate was 30 mL/min, the flame height increased by 25.2%, and the flame temperature increased by about 11.3%.

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Ignition and combustion characteristics of magnesium-based nanofluid fuel

Zhao,

Chen,

Yang

et al. 2024

Acta Astronautica

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Experimental study on thermal ignition and combustion of droplet of ammonium dinitramide based liquid propellant in different oxidizing gas atmospheres

Cited by 18 publications

References 20 publications

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

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

Experimental Study on Microwave-Assisted Ignition and Combustion Characteristics of ADN-Based Liquid Propellant

Ignition and combustion characteristics of magnesium-based nanofluid fuel

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