Development of Hydrogen Peroxide Monopropellant Rockets

Cervone, Angelo; Torre, Lucio; d’Agostino, Luca; Musker, Antony J.; Roberts, G.T.; Bramanti, Cristina; Saccoccia, G.

doi:10.2514/6.2006-5239

Cited by 37 publications

(26 citation statements)

References 7 publications

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“…A significant number of authors including the previously discussed authors Runckel 20 and Ponzo 21 have investigated the catalytic properties of silver and silver oxides. [23][24][25][26][27][28] A similarly large group has investigated manganese dioxide (MnO 2 ) supported on alumina or titanium dioxide. [29][30][31][32][33][34][35] Results are often conflicting.…”

Section: Development Of Alternative Catalysts For Hydrogen Peroxide Dmentioning

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: Development Of Alternative Catalysts For Hydrogen Peroxide Dmentioning

confidence: 99%

“…Cervone et al, 25 used a base catalyst of 80 mesh silver interchanged with bigger meshes of silver and nickel for added support. Su-LiM & Choong-Won 28 also explored silver screens as a catalyst.…”

Section: Previous Research With Noble Metal-based Catalystsmentioning

confidence: 99%

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

Whitmore¹,

Martinez²,

Merkley³

2018

AAOAJ

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“…Although this particular usage might be controversial 4 , sterilization properties of H2O2 make it an inexpensive and versatile disinfectant in laboratory and medicine. But probably the most spectacular application of hydrogen peroxide is in the rocket industry, where it can be used as a propellant 5 , mixed with another fuel, or as a single compound. Environmental friendliness of H2O2 is associated with the fact that the molecule degrades only to H2O and O2.…”

Section: Motivation and Research Backgroundmentioning

confidence: 99%

“…Values of electrode potentials (E°) at standard conditions (T = 298 K, P = 105 Pa, concentration of all reagents equal 1 M; values are relative to the standard hydrogen electrode) In a best-case scenario of hydrogen peroxide synthesis, we have its generation on both electrodes, that is reduction of oxygen on the cathode and oxidation of water on the anode. This not only gives us high yield of hydrogen peroxide but also simplifies the electrochemical system, which can be made as a single compartment cell.…”

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confidence: 99%

Organic electronic materials for hydrogen peroxide production

Gryszel

2020

Linköping Studies in Science and Technology. Dissertations

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“…Unlike other promising high-energy green monopropellants such as ADN, HAN, and HNF, the decomposition of hydrogen peroxide results in products with relatively low molecular weight. This is an advantage because the operational temperature of the exhaust gases in hydrogen peroxide thrusters can be maintained much lower than that of other green propellants resulting in decreased materials and manufacturing costs [34]. Due to these characteristics, hydrogen peroxide is a relevant propellant option for CubeSats with a significantly reduced cost of manufacturing, storage, and handling when compared to other "green" fuels on the market today.…”

Section: Propulsion Systemsmentioning

confidence: 99%

Development of an Additively Manufactured Microthruster for Nanosatellite Applications

Gagne

2016

54th AIAA Aerospace Sciences Meeting

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Next generation small satellites, also known as nanosatellites, have masses significantly lower than traditional satellites. Including the propellant mass, the total mass of a nanosatellite is often in the range of 1 to 4 kg. These satellites are being developed for numerous applications related to research, defense, and industry. Since their popularity began in the early 2000's, limitations on the downscaling of propulsion systems has proven to be problematic. Due to this, the vast majority of nanosatellite missions have limited lifespans of 90-120 days in low Earth orbit before they reenter the Earth's atmosphere. Although satellites on this scale have little available space for instrumentation, the development in the fields of microsensors, microelectronics, micromachinery, and microfluidics has increased the capabilities of small satellites tremendously. With limited options for primary propulsion and attitude control, nanosatellites would benefit greatly from the development of an inexpensive and easily implemented propulsion system. This work focuses on the development of an additively manufactured chemical propulsion system suitable for nanosatellite primary propulsion and attitude control. The availability of such a propulsion system would allow for new nanosatellite mission concepts, such as deep space exploration, maneuvering in low gravity environments, and formation flying. Experimental methods were used to develop a dual mode microthruster design which can operate in either low impulse, pseudo-monopropellant mode, or high impulse, bipropellant mode. Through the use of a homogeneous catalysis scheme for gas generation, nontoxic propellants are used to produce varying levels of thrust suitable for application in nanosatellite propulsion. The use of relatively benign propellants results in a system which is safe and inexpensive to manufacture, store, transport, and handle. In addition to these advantages, the majority of the propulsion system, including propellant storage, piping, manifolding, reaction chambers, and nozzles can be 3D printed directly into the nanosatellite chassis, further reducing the overall cost of the system. This work highlights the selection process of propellants, catalysts, and nozzle geometry for the propulsion system. Experiments were performed to determine a viable catalyst solution, validate the gas generation scheme, and validate operation of the system.

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Development of Hydrogen Peroxide Monopropellant Rockets

Cited by 37 publications

References 7 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

Organic electronic materials for hydrogen peroxide production

Development of an Additively Manufactured Microthruster for Nanosatellite Applications

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