Preliminary results from HEDGEHOG REXUS project – A sounding rocket experiment on accelerations, vibrations and heat flow

Dąbrowski, Adam; Pelzner, Karol; Krawczuk, Szymon Rafał; Goczkowski, J.; Elwertowska, Agnieszka

doi:10.1016/j.actaastro.2020.07.016

Cited by 5 publications

(2 citation statements)

References 8 publications

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“…REXUS experiments prior to that described herein, included various spaceborne technology demonstrators [8][9][10]. The preliminary results from HEDGEHOG REXUS project -A sounding rocket experiment on accelerations, vibrations and heat flow were described by Dąbrowski et al [11].…”

Section: Introductionmentioning

confidence: 99%

Analysis of a Mechanical Vibration Filter and Amplifier for Sounding Rocket Applications

Dąbrowski¹,

Krawczuk²

2021

Preprint

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Determining the vibration environment is crucial to analyzing a design of any mechanical system, especially such dynamic systems as sounding rockets. Accuracy of measurement using accelerometers could be improved by application of mechanical vibration filtering and amplifying devices. This work presents a theoretical description of a tunable filter and amplifier. Principle of work is provided as well as results from application of the device on a sounding rocket are provided. It is shown that implementation of such devices allowed for enhancing the accuracy of acceleration measurements. Conclusions on future implementations are also provided.

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Section: Introductionmentioning

confidence: 99%

Analysis of a Mechanical Vibration Filter and Amplifier for Sounding Rocket Applications

Dąbrowski¹,

Krawczuk²

2021

Preprint

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“…Data shows the heat flux produced by three nozzles arranged in a triangular bundle are higher than produced by nozzles arranged in a linear bundle, due to plume interaction. In order to design the payloads of the REXUS sounding rocket, Adam et al (2020) carried out an experiment that measured substantial heat flux and vibration accurately. The experiment showed that payload mass impacts the rocket heat transfer through influencing the flight trajectories.…”

Section: Introductionmentioning

confidence: 99%

Afterburning effect on thermal environment of four-engine liquid rockets at different altitudes

Zhou

Bao²,

Sun³

et al. 2021

Engineering Applications of Computational Fluid Mechanics

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The liquid rocket propellant burns inadequately in the combustion chamber; therefore, the exhaust gas reacts with oxygen and the heat that was generated, which in turn affects the thermal environment. By using finite-rate chemical kinetics and discrete ordinates method, the calculation model for the four-engine rocket exhaust flowfield is established, and numerically investigates the afterburning effect on the thermal environment of the engine exhaust plume under different altitudes. The results show that the afterburning reactions have little influence on the Mach number exhaust flow, and the difference between the peak temperatures of reacting and non-reacting flows is less than 5%. However, a significant increase in temperature of the mixing layer can be found, and the afterburning effect on the thermal environment reduces with increases in the flight altitude. At the same altitude, the temperature increment of the reacting flow in the far-field region is higher than that of the near-field region. Moreover, as the flight altitude increases from 15 to 35 km, the increase of the rocket base heat flux caused by the afterburning can vary from 9.4% to 2.7%. The results provide a theoretical basis for the designing of the thermal protection systems of multi-engine rockets.

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Effect of high-intensity vibration parameter on droplet transport characteristics in gas channel of proton exchange membrane fuel cell

Zhou,

Ye,

et al. 2024

International Communications in Heat and Mass Transfer

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Preliminary results from HEDGEHOG REXUS project – A sounding rocket experiment on accelerations, vibrations and heat flow

Cited by 5 publications

References 8 publications

Analysis of a Mechanical Vibration Filter and Amplifier for Sounding Rocket Applications

Analysis of a Mechanical Vibration Filter and Amplifier for Sounding Rocket Applications

Afterburning effect on thermal environment of four-engine liquid rockets at different altitudes

Effect of high-intensity vibration parameter on droplet transport characteristics in gas channel of proton exchange membrane fuel cell

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