Preliminary tests on thermal ignition of ADN-based liquid monopropellants

Wilhelm, Marius; Negri, Michele; Ciezki, Helmut; Schlechtriem, Stefan

doi:10.1016/j.actaastro.2018.05.057

Cited by 40 publications

(21 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In addition to potential toxicity and objective hazards, there exist several key developmental issues that make them IL-based propellants unsuitable for some small spacecraft applications. In order to reduce the decomposition hazard, both the LMP-103S and AFM-315E mono-propellants require a significant water content to keep the IL-salts in solution with up to 14% for LMP-103S [13], and 16% for AFM-315E [14]. The high water content makes IL-propellants notoriously hard to ignite.…”

Section: Ionic Liquid Propellantsmentioning

confidence: 99%

Nytrox as “Drop-in” Replacement for Gaseous Oxygen in SmallSat Hybrid Propulsion Systems

Whitmore

2020

Aerospace

View full text Add to dashboard Cite

A medical grade nitrous oxide (N2O) and gaseous oxygen (GOX) “Nytrox” blend is investigated as a volumetrically-efficient replacement for GOX in SmallSat-scale hybrid propulsion systems. Combined with 3-D printed acrylonitrile butadiene styrene (ABS), the propellants represent a significantly safer, but superior performing, alternative to environmentally-unsustainable spacecraft propellants like hydrazine. In a manner analogous to the creation of soda-water using dissolved carbon dioxide, Nytrox is created by bubbling GOX under pressure into N2O until the solution reaches saturation. Oxygen in the ullage dilutes N2O vapor and increases the required decomposition energy barrier by several orders of magnitude. Thus, risks associated with inadvertent thermal or catalytic N2O decomposition are virtually eliminated. Preliminary results of a test-and-evaluation campaign are reported. A small spacecraft thruster is first tested using gaseous oxygen and 3-D printed ABS as the baseline propellants. Tests were then repeated using Nytrox as a “drop-in” replacement for GOX. Parameters compared include ignition reliability, latency, initiation energy, thrust coefficient, characteristic velocity, specific impulse, combustion efficiency, and fuel regression rate. Tests demonstrate Nytrox as an effective replacement for GOX, exhibiting a slightly reduced specific impulse, but with significantly higher volumetric efficiency. Vacuum specific impulse exceeding 300 s is reported. Future research topics are recommended.

show abstract

Section: Ionic Liquid Propellantsmentioning

confidence: 99%

Nytrox as “Drop-in” Replacement for Gaseous Oxygen in SmallSat Hybrid Propulsion Systems

Whitmore

2020

Aerospace

View full text Add to dashboard Cite

show abstract

“…The catalyst bed design is a complicated process and its analysis is out of the scope of this work. Wilhelm et al [30] have found that thermal ignition using a glowplug yields a stable flame and an acceptable ignition time for FLP-106 propellant. An exothermic reaction that corresponds to ADN decomposition starts at 150°C [31].…”

Section: Thruster Performance and Designmentioning

confidence: 99%

“…Here, the residence time t s = 0.0026 s corresponds to the characteristic length L * = 1.5 m, which in turn yields the maximum combustion performance [28,30]. The chamber and nozzle design parameters are listed in Table 4.…”

Section: °Cmentioning

confidence: 99%

Combined Chemical–Electric Propulsion for a Stand-Alone Mars CubeSat

Mani

Cervone

Topputo

2019

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

Stand-alone interplanetary CubeSats require primary propulsion systems for orbit maneuvering and precise trajectory control. The current work focuses on the design and performance characterization of the combined chemical-electric propulsion systems that shall enable a stand-alone 16U CubeSat mission on a hybrid high-thrust-low-thrust trajectory from a Supersynchronous Geostationary Transfer Orbit to a circular orbit about Mars. The high-thrust chemical propulsion is used to escape Earth and to initiate stabilization at Mars. The low-thrust electric propulsion is used in heliocentric transfer, ballistic capture, and circularization. For chemical propulsion, design and performance characteristics of a monopropellant thruster and feed system utilizing ADN-based FLP-106 propellant are presented. For electric propulsion, a performance model of an Iodine-propelled inductively coupled miniature radiofrequency ion thruster is implemented to calculate the variation of thrust, specific impulse and efficiency with input power. A power constrained low-thrust trajectory optimization utilizing the thruster performance model is pursued to calculate the transfer time, ∆V and the required propellant mass for fuel-optimal and time-optimal transfers. Overall, the combined chemical-electric systems yield a feasible propulsion solution for stand-alone CubeSat missions to Mars that balances propellant mass and transfer time.

show abstract

“…Preliminary results of the studies on thermal ignition have been presented in ref. [10]. In the present work the results of numerous hot firing tests with different combustion chambers designed to facilitate ignition are presented.…”

Section: Introductionmentioning

confidence: 99%

Thermal Ignition of ADN‐Based Propellants

Negri

Wilhelm

Ciezki

2019

Propellants Explo Pyrotec

Self Cite

View full text Add to dashboard Cite

Ammonium dinitramide (ADN, NH4+ N(NO2)2−) based monopropellants are extremely promising as hydrazine replacement. Thermal igniters are attractive for ADN thrusters as they allow a more prompt ignition and may be better suited for larger engines (100‐500 N) compared to the currently used preheated catalysts. The results of an experimental campaign conducted on the ignition of two ADN‐based monopropellants (LMP‐103S and FLP‐106) with a torch igniter are presented. Several combustion chamber configurations have been tested to facilitate the ignition. Through the use of porous inlays in the chamber, ignition of both propellants was achieved. It was not possible, however, to achieve sustained combustion under the chosen test conditions.

show abstract

Preliminary tests on thermal ignition of ADN-based liquid monopropellants

Cited by 40 publications

References 1 publication

Nytrox as “Drop-in” Replacement for Gaseous Oxygen in SmallSat Hybrid Propulsion Systems

Nytrox as “Drop-in” Replacement for Gaseous Oxygen in SmallSat Hybrid Propulsion Systems

Combined Chemical–Electric Propulsion for a Stand-Alone Mars CubeSat

Thermal Ignition of ADN‐Based Propellants

Contact Info

Product

Resources

About