Description of the Sounding Rocket Experiment—SOURCE

Fuhrmann, Eckart; Dreyer, Michael

doi:10.1007/s12217-008-9017-4

Cited by 10 publications

(5 citation statements)

References 4 publications

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“…The contact angle γ M yields 35 • shortly after the filling period and 29 • after 105 s. This deformation is caused by the thermocapillary flow away from the contact line towards the center of the test cell. More information about the experiment, the operational scenario and the thermal analysis can be found in Fuhrmann and Dreyer (2008a).…”

Section: Methodsmentioning

confidence: 99%

Heat Transfer by Thermo-Capillary Convection

Fuhrmann

Dreyer

2009

Microgravity Sci. Technol.

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This paper describes the results of a sounding rocket experiment which was partly dedicated to study the heat transfer from a hot wall to a cold liquid with a free surface. Natural or buoyancy-driven convection does not occur in the compensated gravity environment of a ballistic phase. Thermo-capillary convection driven by a temperature gradient along the free surface always occurs if a non-condensable gas is present. This convection increases the heat transfer compared to a pure conductive case. Heat transfer correlations are needed to predict temperature distributions in the tanks of cryogenic upper stages. Future upper stages of the European Ariane V rocket have mission scenarios with multiple ballistic phases. The aims of this paper and of the COMPERE group (French-German research group on propellant behavior in rocket tanks) in general are to provide basic knowledge, correlations and computer models to predict the thermo-fluid behavior of cryogenic propellants for future mission scenarios. Temperature and surface location data from the flight have been compared with numerical calculations to get the heat flux from the wall to the liquid. Since the heat flux measurements along the walls of the transparent test cell were not possible, the analysis of the heat transfer coefficient relies therefore on the numerical modeling which was validated with the flight data. The coincidence between experiment and simulation is fairly good and allows presenting the data in form of a Nusselt number which depends on a characteristic E. Fuhrmann · M. Dreyer (B)

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Section: Methodsmentioning

confidence: 99%

Heat Transfer by Thermo-Capillary Convection

Fuhrmann

Dreyer

2009

Microgravity Sci. Technol.

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“…A microgravity environment can be created by several ground-based facilities, such as the well-known free-fall tower, which may provide 4-6 s of microgravity [3]. Flight vehicles, such as aircraft in parabolic flight [4] and sounding rocket in sub-orbital flight [5], are capable of providing a long time interval (e.g. 20-30 s) of microgravity.…”

Section: Liuwei@csuaccnmentioning

confidence: 99%

Control performance simulation and tests for Microgravity Active vibration Isolation System onboard the Tianzhou-1 cargo spacecraft

Liu

Zhang

et al. 2018

Astrodyn

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The Microgravity Active vibration Isolation System (MAIS), which was onboard China's first cargo-spacecraft Tianzhou-1 launched on April 20, 2017, aims to provide high-level microgravity at an order of 10 −5 -10 −6 g for specific scientific experiments. MAIS is mainly composed of a stator and a floater, and payloads are mounted on the floater. Sensing relative motion with respect to the stator fixed on the spacecraft, the floater is isolated from vibration on the stator via control forces and torques generated by electromagnetic actuators. This isolation results in a high-level microgravity environment. Before MAIS was launched into space, its control performance had been simulated on computers and tested by air-bearing platform levitation and aircraft parabolic flight. This article first presents an overview of the MAIS's hardware system, particularly system structure, measurement sensors, and control actuators. Its system dynamics, state estimation, and control laws are then discussed, followed by the results of computer simulation and engineering tests, including the test of the six-degree-of-freedom motion by aircraft parabolic flight. Simulation and test results verify the accuracy of the control strategy design, effectiveness of the control algorithms, and performance of the entire control system, paving the way for operation of MAIS in space.This article also presents the steps recommended for the control performance simulation and tests of MAIS-like devices. These devices are expected to be used on China's Space Station for various scientific experiments that require a high-level microgravity environment. KEYWORDS

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“…For these reasons, researchers have devoted great efforts to developing ground-based low-gravity simulators. One major category, which utilizes free fall to generate near-zero gravity, includes drop towers 19 , 20 , parabolic aircraft 21 , 22 , sounding rockets 23 , and suborbital rocketry 24 . Despite their usefulness, a known limitation of these facilities is the relatively short low-gravity duration (i.e., from several seconds to a few minutes 25 ), which makes them unsuitable for experiments that require long observation times 26 .…”

Section: Introductionmentioning

confidence: 99%

A magnetic levitation based low-gravity simulator with an unprecedented large functional volume

Sanavandi

Guo

2021

npj Microgravity

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Low-gravity environment can have a profound impact on the behaviors of biological systems, the dynamics of fluids, and the growth of materials. Systematic research on the effects of gravity is crucial for advancing our knowledge and for the success of space missions. Due to the high cost and the limitations in the payload size and mass in typical spaceflight missions, ground-based low-gravity simulators have become indispensable for preparing spaceflight experiments and for serving as stand-alone research platforms. Among various simulator systems, the magnetic levitation-based simulator (MLS) has received long-lasting interest due to its easily adjustable gravity and practically unlimited operation time. However, a recognized issue with MLSs is their highly non-uniform force field. For a solenoid MLS, the functional volume V1%, where the net force results in an acceleration <1% of the Earth’s gravity g, is typically a few microliters (μL) or less. In this work, we report an innovative MLS design that integrates a superconducting magnet with a gradient-field Maxwell coil. Through an optimization analysis, we show that an unprecedented V1% of over 4000 μL can be achieved in a compact coil with a diameter of 8 cm. We also discuss how such an MLS can be made using existing high-Tc-superconducting materials. When the current in this MLS is reduced to emulate the gravity on Mars (gM = 0.38g), a functional volume where the gravity varies within a few percent of gM can exceed 20,000 μL. Our design may break new ground for future low-gravity research.

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Description of the Sounding Rocket Experiment—SOURCE

Cited by 10 publications

References 4 publications

Heat Transfer by Thermo-Capillary Convection

Heat Transfer by Thermo-Capillary Convection

Control performance simulation and tests for Microgravity Active vibration Isolation System onboard the Tianzhou-1 cargo spacecraft

A magnetic levitation based low-gravity simulator with an unprecedented large functional volume

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