Low Pressure Ignition Testing of a Hybrid SmallSat Motor

Jens, Elizabeth T.; Karp, Ashley C.; Nakazono, Barry; Williams, Kyle T.; Rabinovitch, Jason; Dyrda, David; Mechentel, Flora S.

doi:10.2514/6.2019-4009

Cited by 7 publications

(8 citation statements)

References 11 publications

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“…Augmented spark igniters or torch igniters have been used with hybrids in several studies. JPL developed a hybrid rocket engine sized for CubeSat satellites with GOX/PMMA propellants and GOX/CH 4 torch igniter and demonstrated 24 successful reignitions in vacuum conditions [15,29].…”

Section: Ignition Methods For In-space Hybridsmentioning

confidence: 99%

“…JPL is working on a hybrid propellant thruster designed for CubeSats that could be accommodated within a 12 U envelope, capable of delivering a ∆v of over 200 m/s to a 25 kg spacecraft [14]. The 40 N thruster uses a GOX/PMMA propellant mix and an augmented GOX/methane spark igniter and has demonstrated successful vacuum condition tests with multiple reignitions, achieving over 300 s of specific impulse [15]. NASA Ames has conducted many tests on their 25 N hybrid for small spacecraft, a project that spanned several years [16].…”

Section: Introduction 1hybrid Rocket Engines For In-space Applicationsmentioning

confidence: 99%

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Testing of the N2O/HDPE Vortex Flow Pancake Hybrid Rocket Engine with Augmented Spark Igniter

Palacz,

Cieślik

2023

Aerospace

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The paper is part of the research aimed at determining if the vortex flow pancake (VFP) hybrid rocket engine is feasible as green in-space chemical propulsion. The objective of this study is to test an N2O/HDPE VFP hybrid ignited with N2O/C3H8 torch igniter. The N2O is used in self-pressurizing mode, which results in two-phase flow and varying inlet conditions, thus better simulating real in-space behavior. The study begins with characterizing the torch igniter, followed by hot-fire ignition tests of the VFP. The results allow for the improved design of the torch igniter and VFP hybrid. The axial regression rate ballistic coefficients are reported for the N2O/HDPE propellants in the VFP configuration.

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Section: Ignition Methods For In-space Hybridsmentioning

confidence: 99%

Section: Introduction 1hybrid Rocket Engines For In-space Applicationsmentioning

confidence: 99%

Testing of the N2O/HDPE Vortex Flow Pancake Hybrid Rocket Engine with Augmented Spark Igniter

Palacz,

Cieślik

2023

Aerospace

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“…[3][4][5][6][7][8] Adding to the thrusters using those propellants, the trend of hybrid motors has been spreading. [9][10][11][12][13][14][15][16][17] A hybrid motor has the advantages of safety, based on the chemical stability of both the fuel and the oxidizer, and their separate installation. Whitmore et al developed a hybrid motor that used acrylonitrile butadiene styrene (ABS) as a fuel and a mixture of nitrous oxide and gaseous oxygen as an oxidizer.…”

Section: Introductionmentioning

confidence: 99%

“…[13][14][15][16]18) The prototype was fabricated and tested both in atmosphere and in a vacuum, and worked successfully. [13][14][15][16] Kamps et al conducted a conceptual and experimental study regarding the apogee-motor for 100-kg or lighter satellites adopting high-density polyethylene (HDPE) as a fuel and nitrous oxide as an oxidizer. 17) This system also took advantage of the self-pressurizing property of nitrous oxide.…”

Section: Introductionmentioning

confidence: 99%

“…For hybrid motors, several new ignition systems have been proposed, such as laser, arc-heating, a torch, or the decomposition of an oxidizer using a catalyst other than the conventional one of gunpowder and nichrome wire. 11,12,[14][15][16] This is because a conventional ignition system is not suitable for reignition. Additionally, gunpowder has the problem of the existence of a hazard.…”

Section: Introductionmentioning

confidence: 99%

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Feasibility Study of a Hybrid Thruster using Wire-Shaped Magnesium and Water for Application to Small Spacecraft

Akiyama

Nishii

Mannami

et al. 2021

Trans. Japan Soc. Aero. S Sci.

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High thrust propulsion systems that can be used in small spacecraft are urgently needed to expand the use of small spacecraft. This study proposes a hybrid thruster for small spacecraft using wire-shaped magnesium as a fuel and water as an oxidizer. "Hybrid thruster" means that the in-space propulsion system generates thrust using a chemical reaction between a solid fuel and a vapor oxidizer, such as those utilized for hybrid rockets. Both magnesium and water are very safe, highly available, and very storable. To assess the feasibility of a hybrid thruster, we carried out experiments utilizing magnesium-wire combustion in water vapor at a pressure lower than the atmosphere, and estimated the input power for ignition, ignitability, and the average magnesium mass consumption rate. Then, propulsion performances were calculated using the experimental results, which show there is an input power of 2-3 W, with higher ignitability and a lower average mass consumption rate for thinner magnesium wires. The calculated specific impulse achieved its maximum at 323 s, with a mass mixture ratio of 1.25. At that mass mixture ratio, the calculated thrust using magnesium wires having diameters of 0.5 mm and 0.8 mm was 49.8 mN and 68.5 mN, respectively. Additionally, the applicability of the hybrid thruster was shown through a case study considering an existing deep-space misson.

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Diode Laser Ignition of a Poly(Methyl Methacrylate) and Gaseous Oxygen Hybrid Motor

Dyrda¹,

Mechentel²,

Cantwell³

et al. 2020

Journal of Propulsion and Power

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Low Pressure Ignition Testing of a Hybrid SmallSat Motor

Cited by 7 publications

References 11 publications

Testing of the N2O/HDPE Vortex Flow Pancake Hybrid Rocket Engine with Augmented Spark Igniter

Testing of the N2O/HDPE Vortex Flow Pancake Hybrid Rocket Engine with Augmented Spark Igniter

Feasibility Study of a Hybrid Thruster using Wire-Shaped Magnesium and Water for Application to Small Spacecraft

Diode Laser Ignition of a Poly(Methyl Methacrylate) and Gaseous Oxygen Hybrid Motor

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