The Nammo Nucleus Launch: Norwegian Hybrid Sounding Rocket over 100km

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

doi:10.2514/6.2019-4049

Cited by 20 publications

(7 citation statements)

References 1 publication

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“…In the last decade, researches on liquefying fuels revived the interest of the scientific community which is currently focusing on paraffin-wax, a valuable candidate as a propellant thanks to its many benefits such as availability, safety, cost-effectiveness, and ballistic properties. Paraffin-based hybrid propulsion capabilities have been proven by many demonstrators, sounding rocket launches, and test facilities [8,17]; therefore, there is a great interest in using HREs in place of the commonly employed solid-propellant and liquid-propellant engines for specific applications, like main engines in suborbital vehicles [3] or upper stages of small rockets [6].…”

Section: Introductionmentioning

confidence: 99%

A Computational Tool for the Design of Hybrid Rockets

Zolla

Migliorino

Bianchi

et al. 2021

Aerotec. Missili Spaz.

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A computational tool able to perform a fast analysis of hybrid rocket engines is presented, describing briefly the mathematical and physical models used. Validation of the code is also shown: 16 different static firing tests available in the open literature are used to compare measured operational parameters such as chamber pressure, thrust, and specific impulse with the code’s output. The purpose of the program is to perform rapid evaluation and assessment on a possible first design of hybrid rockets, without relying on computationally expensive simulations or onerous experimental tests. The validated program considers as benchmark and study case the design of a liquid-oxygen/paraffin hybrid rocket engine to be used as the upper stage of a small launcher derived from VEGA building blocks. A full-factorial parametric analysis is performed for both pressure-fed and pump-fed systems to find a configuration that delivers the equivalent total impulse of a VEGA-like launcher third and fourth stage as a first evaluation. This parametric analysis is also useful to highlight how the oxidizer injection system, the fuel grain design, and the nozzle features affect the performance of the rocket.

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Section: Introductionmentioning

confidence: 99%

A Computational Tool for the Design of Hybrid Rockets

Zolla

Migliorino

Bianchi

et al. 2021

Aerotec. Missili Spaz.

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“…Another example of a flight-tested hybrid sounding rocket with a similar specific impulse performance is Nucleus of Nammo [55]. This was a single-stage sounding rocket producing a 30 kN class thrust with a burn time of 39 s and propellant fraction of 0.59.…”

Section: Resultsmentioning

confidence: 99%

A practical design approach for a single-stage sounding rocket to reach a target altitude

Huh

Kwon

2022

Aeronaut. j.

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A new type of design domain for a sounding rocket is suggested in this study, which is more intuitive, simplified, and conducive to a single-stage sounding rocket development process. Among the various operation parameters, this study identifies several effective variables, which are also among the most practical in a sounding rocket design process. Of the many design variables considered for peak altitude optimisation, arguably the three most effective in shaping the whole system and conferring the most practicality in the design process of a sounding rocket were determined. A simulation-based study was conducted to establish: the effect of the selected parameters on flight performance, and the optimum design conditions of a single-stage sounding rocket in terms of its peak altitude. The simulation result was compared with randomly chosen experimentally tested flight data and validated. With the clear performance curves varying depending on the variables, the combination of the considered design inputs was effective. The new type of design domain and design procedure proposed is expected to constitute a useful reference and deliver practical benefits to the development process for a target-altitude-optimised single-stage sounding rocket.

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“…While most of the historical suborbital rockets utilized solid rocket motors such as military surplus motors (NASA, 2019), modern solutions often make use of liquid propellants as is the case for Nucleus (Faenza et al,2019), MIURA-1 (Francisco et al, 2018), ILR-33 AM-BER (Marciniak et al, 2018) and New Shepard (Blue Origin, 2019). The latter is an interesting example of a rocket with a demonstrated reusability and ability to land using its propulsion system -similarly as is done with Falcon 9 launch vehicles.…”

Section: Suborbital Launch Vehicles -Their Construction and Applications In Civil Sectormentioning

confidence: 99%

Suborbital rockets in safety & defense applications

Noga

2021

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This paper presents benefits from using suborbital rockets in safety & defense applications. The paper describes suborbital rockets and their contribution to modern science, research and technology development. A historical view of suborbital rockets and their applications in safety & defense roles is discussed. Chosen research & development activities, military exercises and air defense systems’ tests performed using suborbital rockets in various countries are listed and described based on a literature review of publicly available sources. The paper presents capabilities of Łukasiewicz Research Network – Institute of Aviation in the field of suborbital rockets. A development of ILR-33 AMBER 2K rocket reaching flight speeds over Mach 4 and optimized to reach 100 km altitude is described with comment regarding its applicability in safety & defense applications supported by flight simulations.

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The Nammo Nucleus Launch: Norwegian Hybrid Sounding Rocket over 100km

Cited by 20 publications

References 1 publication

A Computational Tool for the Design of Hybrid Rockets

A Computational Tool for the Design of Hybrid Rockets

A practical design approach for a single-stage sounding rocket to reach a target altitude

Suborbital rockets in safety & defense applications

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