Performances of a Multi-Pulsed Hybrid Rocket Engine Operating with Highly Concentrated Hydrogen Peroxide

Anthoine, J.; Lestrade, Jean-Yves; Messineo, Jérôme; Casu, Santiago

doi:10.2514/6.2017-4906

Cited by 12 publications

(10 citation statements)

References 9 publications

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“…Following guidance offered by Anthione et al, 15 a hollow-cone injector swirl injector was used in order to effectively atomize the peroxide flow and provide for positive impingement against the fuel port walls. In order to evenly mix the ignitor GOX flow into the peroxide stream, a symmetrically-distributed GOX injector was machined into the motor cap.…”

Section: Peroxide and Gox Injector Designsmentioning

confidence: 99%

Catalyst development for an arc-ignited hydrogen peroxide/ABS hybrid rocket system

Whitmore¹,

Martinez²,

Merkley³

2018

AAOAJ

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The authors have collaborated with an industry partner to develop a prototype upper stage for a dedicated nano-launch vehicle. In addition to providing sufficient impulse for orbit insertion, the unique motor system also provides capability for multiple restarts; allowing operation as an orbital maneuvering thruster. The hybrid motor design uses 85%-90% hydrogen peroxide solution and 3-D printed ABS (acrylonitrilebutadiene-styrene) as propellants. In the original system design the peroxide catalyst bed was completely removed and a patented arc-ignition system thermally ignited the propellants. The thermal ignition system was effective but resulted in a combustion latency of approximately 1-second, reducing overall performance and allowing for significant variability in the delivered total impulse. This work investigates whether adding a small catalyst pack for ignition augmentation can eliminate or significantly reduce the observed ignition latency and improve overall system performance. The effectiveness of multiple catalytic minerals including potassium permanganate, manganese dioxide, manganese (III) oxide, and potassium nitrate were examined and compared to traditional noble-metal catalyst materials like silver or platinum. These alternative materials are significantly less expensive than noble metals. Catalytic activity test results, designs for an augmentation catbed integrated with the thermal ignition system, and preliminary unaugmented and augmented hot-fire test results are presented. Aeronautics and Aerospace Open Access Journal Research Article Open AccessCatalyst development for an arc-ignited hydrogen peroxide/ABS hybrid rocket system 357

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Section: Peroxide and Gox Injector Designsmentioning

confidence: 99%

Catalyst development for an arc-ignited hydrogen peroxide/ABS hybrid rocket system

Whitmore¹,

Martinez²,

Merkley³

2018

AAOAJ

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“…Recently, several groups and organizations including the Bloodhound SSC (OK) c supersonic car team, ONERA (France) [28], and Nammo Raufoss (Norway), [29] and have tested H 2 O 2 as an oxidizer in hybrid rocket systems. These projects P chamber /P catbed < 0.55 for 90% peroxide, then a decomposition efficiency of near 93% is required to maintain the chamber temperature above the pyrolysis temperature of ABS.…”

Section: Previous Applications Of Hydrogen Peroxide In Hybrid Rocketsmentioning

confidence: 99%

Direct Ignition of a High Performance Hydrogen Peroxide Hybrid Rocket with 3-D Printed Fuel

A¹

2019

Int J Astronaut Aeronautical Eng

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Development of a high-performing hybrid rocket system that employs 90% hydrogen peroxide and 3-D printable thermoplastic materials is reported. Traditionally, high-grade peroxide has been employed as a monopropellant using noble-metal catalysts to initiate thermal decomposition. Catbeds beds are expensive, heavy, and contribute no propulsive mass to the system. Catbeds exhibit limited operational lifetimes, and are often rendered inactive due to the high temperatures of thermal decomposition. The presented alternative thermallydecomposes the injected peroxide stream using an electrostatic ignition system, where as a moderate electric field is introduced to the additively layered ABS fuel grain. Electrostatic arcs are induced within the 3-D printed surface features, and produce sufficient pyrolyzed fuel vapor to induce spontaneous combustion when a flow of gaseous oxygen is introduced. Heat released is sufficient to thermally decompose the injected peroxide stream. The liberated heat and oxygen from decomposition drive full combustion along the length of the fuel grain. Gaseous oxygen pre-leads as small as 250 ms reliably initiate combustion. Multiple on-demand relights are provided with this system. Achieved laboratory specific impulse values exceed 215 s under ambient conditions, with a projected vacuum value exceeding 300 s. Density specific impulse values exceeding 4000 N-s/liter are achievable with this system.

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“…Larger pressure oscillations occurred for axial injector case compared with the swirl injector case in which mixing is enhanced between the hot gaseous oxidizer and the pyrolyzed fuel [3]. The temperature recorded at the outlet of the decomposition temperature reaches about 875 K, just before the extinction of the engine.…”

Section: Fig 8 Firing Test With Catalyzer and The Axial Gaseous Injementioning

confidence: 95%

“…The HYCAT facility is made up of four parts (figure 5): a catalyzer injector, a combustion chamber, a post-chamber and a nozzle. This facility was designed to be able to change the length of each engine part and the fuel grain type [3]. Even though different propellants can be used, those involved in this paper are HDPE for the fuel and h 2 O 2 for the oxidizer.…”

Section: Experimental Set-upmentioning

confidence: 99%

“…In this case, the solid fuel is cast in the combustion chamber as for the solid rocket motor technology whereas the oxidizer is stored in a proper tank as in the liquid propulsion technology. The convective and radiative heat fluxes stemming from the diffusion flame provide the energy needed for the solid grain pyrolysis in order to sustain heterogeneous combustion [2,3]. Such a cycle makes from hybrid combustion a self-sustained phenomenon which occurs as a macroscopic diffusion flame.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Study of Fuel Regression in Hybrid Rocket Engine

Durand¹,

Raynaud²,

Lamet³

et al. 2018

2018 Joint Propulsion Conference

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Performances of a Multi-Pulsed Hybrid Rocket Engine Operating with Highly Concentrated Hydrogen Peroxide

Cited by 12 publications

References 9 publications

Catalyst development for an arc-ignited hydrogen peroxide/ABS hybrid rocket system

Catalyst development for an arc-ignited hydrogen peroxide/ABS hybrid rocket system

Direct Ignition of a High Performance Hydrogen Peroxide Hybrid Rocket with 3-D Printed Fuel

Numerical Study of Fuel Regression in Hybrid Rocket Engine

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