Hybrid Rocket Motor Upscaling and Development Test Campaign at Nammo Raufoss

Boiron, Adrien J.; Verberne, Onno; Faenza, Martina; Haemmerli, Bastien

doi:10.2514/6.2015-4044

Cited by 6 publications

(2 citation statements)

References 3 publications

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“…A sub-orbital hybrid sounding rocket is in development by the Norwegian company NAMMO. 33,34) The engine is using a HTPB fuel and Hydrogen Peroxide (H 2 O 2 ) as oxidizer. The Jet Propulsion Laboratory is currently evaluating hybrid rocket propulsion as a technology for a Mars Ascent Vehicle.…”

Section: Recent and Current Programsmentioning

confidence: 99%

A Record Flight of the Hybrid Sounding Rocket HEROS 3

Kobald¹,

Schluechter²,

Fischer³

et al. 2018

AEROSPACE TECHNOLOGY JAPAN

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Hybrid rocket propulsion offers inherent safety during handling and launch operations at low cost. This makes it not only attractive for space tourism applications like SpaceShipTwo but also for sounding rockets and for educational activities with students. This has been successfully demonstrated by the HyEnD student project from the University of Stuttgart: On November 8 th , 2016 at 10:30 a.m. the hybrid sounding rocket HEROS 3 was launched from the Esrange Space Center to an apogee altitude of 32,300 m (106,000 ft). This set a new altitude record for European student and amateur rocketry. Furthermore, this is a world altitude record for hybrid rockets built by students. It was successfully recovered with the drogue and main parachute being released. The rocket was powered by a 10 kN design thrust hybrid rocket engine with a paraffin-based fuel and Nitrous Oxide (N 2 O) as the oxidizer. The combustion efficiency was verified to be above 97 % in ground tests. Liquid burn time in the flight was for 15 s with an additional combustion of gaseous N 2 O in the blow-down mode of about 10 s. The rocket was 7.5 m long with an empty mass of about 75 kg. The rocket structure was made completely from light-weight carbon fibre and glass fibre reinforced plastic.

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Section: Recent and Current Programsmentioning

confidence: 99%

A Record Flight of the Hybrid Sounding Rocket HEROS 3

Kobald¹,

Schluechter²,

Fischer³

et al. 2018

AEROSPACE TECHNOLOGY JAPAN

View full text Add to dashboard Cite

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“…There is a hybrid rocket which is economical, safe, and reliable, and it is an attractive choice for space propulsion as it has the advantages of both solid and liquid rocket propulsion systems. Many previous hybrid rocket applications [8][9][10][11][12][13][14][15][16], from lab-based sounding rockets to spaceships, demonstrate their advantages.…”

Section: Introductionmentioning

confidence: 99%

Preliminary Assessment of Hydrogen Peroxide Gel as an Oxidizer in a Catalyst Ignited Hybrid Thruster

Huh

Jyoti

Yun

et al. 2018

International Journal of Aerospace Engineering

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In regard to propulsion system applications, the stability of liquid propellants in long-term storage is of increasing importance, and this had led to a greater interest in gelation technology. As part of a preliminary test to determine the feasibility of using a gel propellant in a rocket with a catalyst bed, a hybrid rocket with a catalyst reactor using a gel propellant as an oxidizer was tested for the first time in this study. Experiments were conducted with two different oxidizers: one with liquid phase hydrogen peroxide and the other with gel phase hydrogen peroxide, as well as high-density polyethylene as fuel for a 250 N class hybrid thruster performance test. The thruster was designed with the catalyst ignition system, and a catalyst was manufactured to be inserted into the catalyst reactor to facilitate oxidizer decomposition. While the test result with neat hydrogen peroxide indicated sufficient decomposition efficiency using a manganese dioxide/alumina catalyst and successful autoignition of the fuel via the decomposed product, gel hydrogen peroxide exhibited insufficient decomposition and there were difficulties in operating the thruster as a part of the catalyst was covered in the gelling agent. This preliminary study identifies the potential challenges of using a gel phase oxidizer in a catalyst ignited hybrid thruster and discusses the technical issues that should be addressed in regard to a gel propellant hybrid thruster design with a catalyst reactor.

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