High-Performing Hydrogen Peroxide Hybrid Rocket with 3-D Printed and Extruded ABS Fuel

Whitmore, Stephen A.; Armstrong, Isaac W.; Heiner, Mark C.; Martinez, Christopher J.

doi:10.2514/6.2018-4443

Cited by 9 publications

(9 citation statements)

References 16 publications

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“…As described previously, the initial phase of the development campaign examined various hardware permutation in order to understand the configuration elements that were essential to establishing reliable and repeatable ignition sequences using only thermal ignition. 16 During this testing campaign, the GOX valve and ignition spark were was set to pre-lead the peroxide valve opening by 2 seconds. The GOX valve would remain open for two seconds after the peroxide valve was opened.…”

Section: Summary Of Initial Peroxide/abs Arc-ignition Test Resultsmentioning

confidence: 99%

“…The resulting chamber pressure varied over a range from 160 to 200 psia. Whitemore et al, 6,16 describe the test apparatus and procedures in detail. All tests were performed at ambient pressure background conditions.…”

Section: Summary Of Initial Peroxide/abs Arc-ignition Test Resultsmentioning

confidence: 99%

“…The catalyst bed holder of Figure 12 was installed the just upstream of the injector cap. In order to aid catalycity a 100-watt external band heater 16 was also installed around the catbed holder. The system uses nitrogen as a pressurant and carbon dioxide to operate all of the pneumatic ball valves.…”

Section: Warm Flow and Hot Fire Test Campaignsmentioning

confidence: 99%

“…The catbed inlet and outlet pressures and the motor head-end chamber pressure are also measured. The flow temperature at the catbed outlet is sensed 16 1-Piece Mica Insulated Band Heater.…”

Section: Warm Flow and Hot Fire Test Campaignsmentioning

confidence: 99%

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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: Summary Of Initial Peroxide/abs Arc-ignition Test Resultsmentioning

confidence: 99%

Section: Summary Of Initial Peroxide/abs Arc-ignition Test Resultsmentioning

confidence: 99%

Section: Warm Flow and Hot Fire Test Campaignsmentioning

confidence: 99%

“…The catbed inlet and outlet pressures and the motor head-end chamber pressure are also measured. The flow temperature at the catbed outlet is sensed 16 1-Piece Mica Insulated Band Heater.…”

Section: Warm Flow and Hot Fire Test Campaignsmentioning

confidence: 99%

See 2 more Smart Citations

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

Whitmore¹,

Martinez²,

Merkley³

2018

AAOAJ

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“…Another trend considers additive manufacturing of fuel grains. Recent tests of additively manufactured fuel grains with HTP are discussed in [44,45,53]. This includes hot-firing tests of additively manufactured grains with 98% HTP, where ABS, HDPE and PA6 were tested as fuel [44].…”

Section: Introductionmentioning

confidence: 99%

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

et al. 2021

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This paper presents the development of indigenous hybrid rocket technology, using 98% hydrogen peroxide as an oxidizer. Consecutive steps are presented, which started with interest in hydrogen peroxide and the development of technology to obtain High Test Peroxide, finally allowing concentrations of up to 99.99% to be obtained in-house. Hydrogen peroxide of 98% concentration (mass-wise) was selected as the workhorse for further space propulsion and space transportation developments. Over the course nearly 10 years of the technology’s evolution, the Lukasiewicz Research Network—Institute of Aviation completed hundreds of subscale hybrid rocket motor and component tests. In 2017, the Institute presented the first vehicle in the world to have demonstrated in-flight utilization for 98% hydrogen peroxide. This was achieved by the ILR-33 AMBER suborbital rocket, which utilizes a hybrid rocket propulsion as the main stage. Since then, three successful consecutive flights of the vehicle have been performed, and flights to the Von Karman Line are planned. The hybrid rocket technology developments are described. Advances in hybrid fuel technology are shown, including the testing of fuel grains. Theoretical studies and sizing of hybrid propulsion systems for spacecraft, sounding rockets and small launch vehicles have been performed, and planned further developments are discussed.

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N2O/O2 blends safe and volumetrically efficient oxidizers for small spacecraft hybrid propulsion

Whitmore¹,

Stoddard²

2019

AAOAJ

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A medical grade nitrous oxide and gaseous oxygen fluid blend, "Nytrox," is investigated as significantly safer, but superior performing, alternative for the current generation of environmentally unsustainable spacecraft propellants. In a manner directly analogous to the creation of soda-water using dissolved carbon dioxide, Nytrox is created by bubbling gaseous oxygen under high pressure into nitrous oxide until the solution reaches saturation level. Oxygen in the ullage vapor dilutes the nitrous oxide vapor and increases the required decomposition activation energy of the fluid by several orders of magnitude. Consequently, any risk of inadvertent thermal or catalytic decomposition is virtually eliminated. This paper reports on a preliminary test-and-evaluation campaign where an existing small spacecraft thruster is first tested using gaseous oxygen and 3-D printed ABS as propellants as a baseline. The baseline tests were then repeated using an optimized Nytrox bend as "drop-in" replacement for gaseous oxygen. Test parameters compared include; ignition reliability and required energy, thrust coefficient, characteristic velocity, specific impulse, and fuel regression rate. Nytrox is shown to work effectively and reliably as a replacement for gaseous oxygen, exhibiting a slightly reduced specific impulse and regression rate, but with significantly higher volumetric efficiency. Recommended topics for future research are discussed.

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High-Performing Hydrogen Peroxide Hybrid Rocket with 3-D Printed and Extruded ABS Fuel

Cited by 9 publications

References 16 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

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

N2O/O2 blends safe and volumetrically efficient oxidizers for small spacecraft hybrid propulsion

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