Experimental testing of mini heat pipes under microgravity conditions aboard a suborbital rocket

Paiva, K.V.; Mantelli, Marcia; Slongo, Leonardo Kessler

doi:10.1016/j.ast.2015.06.004

Cited by 28 publications

(13 citation statements)

References 8 publications

(10 reference statements)

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“…when the evaporator above the condenser). Mantelli et al [12] provided a similar conclusion testing a planar copper tube PHP (sixteen turns, 1.27 mm I.D. ), on a suborbital sounding rocket flight.…”

Section: Introductionmentioning

confidence: 65%

A pulsating heat pipe for space applications: Ground and microgravity experiments

Mangini

Mameli

Georgoulas

et al. 2015

International Journal of Thermal Sciences

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Section: Introductionmentioning

confidence: 65%

A pulsating heat pipe for space applications: Ground and microgravity experiments

Mangini

Mameli

Georgoulas

et al. 2015

International Journal of Thermal Sciences

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“…However, by looking carefully at the results, the increase of performance was evident only for the THM, while the gravity assisted one does not show a sensible temperature reduction during the parabolas. De Paiva et al designed and tested a PHP on ground and in a Sounding Rocket Campaign [12,13]. The device, partially filled up with acetone (FR=50%), had 16 turns at the evaporator, while the overall dimensions were 270 x 90 x 250 mm 3 .…”

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confidence: 99%

Hybrid Pulsating Heat Pipe for space applications with non-uniform heating patterns: Ground and microgravity experiments

Mangini

Mameli

Fioriti

et al. 2017

Applied Thermal Engineering

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A hybrid Closed Loop Thermosyphon/Pulsating Heat Pipe with an inner diameter bigger than the capillary threshold is tested both on ground and in hyper/microgravity conditions. The device, partially filled up with FC-72, consists of an aluminum tube (inner diameter: 3 mm) bent into a planar serpentine with five curves at the evaporator. A transparent section closes the loop in the condenser zone, allowing fluid flow visualization. Five heaters are mounted alternatively on the branches, just above the turns and controlled independently, in order to investigate the effect of non-uniform heating configurations. On ground, where the device works as a thermosyphon, the non-uniform heating configurations promote the fluid net circulation in a preferential direction, increasing the thermal performance with respect to the homogeneous heating. Parabolic flights point out that during the 20 seconds of microgravity, the sudden absence of the buoyancy force activates an oscillating slug/plug flow regime, typical of the Pulsating Heat Pipes, allowing the device to work also without the assistance of gravity. Furthermore, peculiar heating configurations can shorten the stop-over periods and stabilize the pulsating two-phase flow motion.

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“…Simultaneously, as a redundant option, the experiments' electronics shall save information in their own internal memory, for the case of accessing them later. From the 120 experience obtained in previous sounding rocket missions, telemetry is also not always fully received and the internal memory may be the only way to obtain the flight data [9] [10].…”

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confidence: 99%

“…135iments) in sounding rockets. We named it the sounding rocket Multi-Mission Platform (MMP), shown in(Figure 2).Besides the capability of testing nanosatellites, the Multi-Mission Platformis intended for scientific thermal experiments[11][10]. The embedded system Rocket and bunker connections…”

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confidence: 99%

Pre-flight qualification test procedure for nanosatellites using sounding rockets

et al. 2019

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et al.. Pre-flight qualification test procedure for nanosatellites using sounding rockets. Acta Astronautica, Elsevier, 2019, 159, pp.Abstract This work presents an innovative procedure to test nanosatellites subsystems on board sounding rockets. The procedure allows the subsystems to save their telemetry data during the whole rocket flight phases (including at the rocket lift-off). The subsystems of the FloripaSat (1U CubeSat) engineering model have been tested on board a VSB-30 rocket in order to validate their design and integration process. A dedicated embedded system has been proposed to operate as an electronic interface between the nanosatellite subsystems and the rocket electronics. Also, a system to process telemetry data was implemented on * Corresponding author Email addresses: slongo@eel.ufsc.br (Leonardo Kessler Slongo), jgreis@lisha.ufsc.br (João Gabriel Reis), daniel.gaiki@studenti.polito.it (Daniel Gaiki), pedro@labtucal.ufsc.br (Pedro Von Hohendorff Seger), sara.vega@posgrad.ufsc.br (Sara Vega Martínez), bruno.eiterer@grad.ufsc.br (Bruno Vale Barbosa Eiterer), tulio.gomes.pereira@grad.ufsc.br (Tulio Gomes Pereira), mario.baldini@posgrad.ufsc.br (Mario Baldini Neto), m.frata@grad.ufsc.br (Matheus dos Santos Frata), henrique.hamisch@grad.ufsc.br (Henrique Daniel Hamisch),Subsystem (EPS); Telemetry, Tracking and Command (TT&C); and On Board Data Handling (OBDH). Several nanosatellites' functions have been evaluated, including: battery monitoring; inertial measurement unit; temperature measurements; radio transceiver; and beacon. The flight results were considerably different from the results obtained at the laboratory. This has allowed important modifications to be made on the design of the CubeSat flight model as the revision on the radio circuit on TT&C and the implementation of an external battery charger circuit for the EPS.Keywords: Test procedure, design validation, nanosatellite, sounding rocket 65 ditions. Even real nanosatellite missions can not provide data to this analysis, since the spacecrafts are placed in the P-POD (or equivalent launching device) during the flight, obligatorily in switch off condition. Laboratory qualification tests are essential, and they may be performed with the satellite subsystems collecting data. However, the physical phenomena are treated separately in 70 each test (vibration, acceleration, mechanical shock, temperature cycling, etc.), and normally, in a lower level of intensity (specially for nanosatellite projects).These are the reasons why this test procedure has been proposed, believing that new data may arise from these suborbital flights, which will help nanosatellite designers in their projects. 75 Besides the procedures of nanosatellite's subsystem configuration and integration, this paper also describes the design of the Multi-Mission Platform (MMP), which is an embedded system conceived to allow nanosatellite tests (and other experiments) aboard sounding rockets. This platform is based on a 4 180 experiment's goal is to test a thermal device, as wel...

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Experimental testing of mini heat pipes under microgravity conditions aboard a suborbital rocket

Cited by 28 publications

References 8 publications

A pulsating heat pipe for space applications: Ground and microgravity experiments

A pulsating heat pipe for space applications: Ground and microgravity experiments

Hybrid Pulsating Heat Pipe for space applications with non-uniform heating patterns: Ground and microgravity experiments

Pre-flight qualification test procedure for nanosatellites using sounding rockets

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