SMARTS Thermal Architecture for PnPSat-2

Bugby, D.; Zimbeck, Walter; Preble, Jeffrey C.; Kroliczek, E. J.

doi:10.1063/1.3326261

Cited by 2 publications

(4 citation statements)

References 1 publication

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“…19 Component-level control includes paraffin-based technologies and variable thermal layers using thermoelectric devices. 32,33 The Space Test Program-Houston 4-Active Thermal Tile (STP-H4-ATT) mission investigated variable conductance thermal tiles that serve as a quick-insert thermal management device for satellite components (Figure 9).…”

Section: Thermal Controlmentioning

confidence: 99%

Enabling Future Spacecraft Missions through Isothermal Bus Thermal Management

Hengeveld

2016

46th AIAA Thermophysics Conference

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The Isothermal Bus architecture is a novel idea focused on approaching a single thermal node S/C representation. In effect, heat is shared efficiently between cold and hot components and in combination with thermal control, spatial and temporal variations in temperature are minimized. The Isothermal Bus can enable higher capability systems along with providing schedule and cost savings. A nominal case study was provided that compared a traditional TCS to the Isothermal Bus concept with a 7:1 switching ratio. While the traditional TCS could accommodate 300 W of bus power, it would require survival heaters. However, the Isothermal Bus concept would enable a 167% increase in bus power while almost eliminating the need for survival heat. I. Nomenclature AI&T= Assembly, Integration, and Test ATT = Active Thermal Tile HTC = High Thermal Conductance ITEMS = Integrated Thermal Energy Management System LEO = Low Earth Orbit MLI = Multilayer Insulation PnP = Plug-and-play OLR = Outgoing Longwave Radiation S/C = Spacecraft SMARTS = Satellite Modular and Reconfigurable Thermal System TCP = Thermal Control Panel TCS = Thermal Control Subsystem VHT = Variable Heat Transfer II. Introduction PACE exploitation provides tremendous opportunities. Since 1957, spacecraft (S/C) have been developed to take advantage of this new high ground by providing communication, scientific observation, weather monitoring, navigation, remote sensing, surveillance, and data-relay services. 1 However, space presents extraordinary challenges. Consequently, S/C have become exceedingly complex and costly. Current S/C can take 1 Senior Engineer, AIAA Senior Member. 2 Senior Mechanical Engineer, Space Vehicles Directorate, AIAA Senior Member. 3 Mechanical Engineer, Space Vehicles Directorate, AIAA Member. S Downloaded by PURDUE UNIVERSITY on June 24, 2016 | http://arc.aiaa.org |

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Section: Thermal Controlmentioning

confidence: 99%

Enabling Future Spacecraft Missions through Isothermal Bus Thermal Management

Hengeveld

2016

46th AIAA Thermophysics Conference

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“…Finally, the complete temperature homogenization between all panels of the satellite can be provided by an additional network of heat pipes at the junction of lateral panels and end panels. This network can be simply a super header heat pipe [74] linking headers of each heat absorbing panels with the dissipating panel (Figure 17.c). In most cases, the thermal system at the radiator panel is here often a two-phase loop, preferable for large heat loads on long transport lengths.…”

Section: Temperature Homogenization Between Panelsmentioning

confidence: 99%

“…A modular architecture [60], called SMARTS (for "Satellite Modular and Reconfigurable Thermal System"), aims to design an efficient two-phase thermal control system for small satellites, within maximum 6 days, taking into account mechanical, electronical and software requirements. [65]), (b) between two adjacent panels with capillary tube network (from [70]), (c) between all the panels with super header pipe (from [74])…”

Section: Temperature Homogenization Between Panelsmentioning

confidence: 99%

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Heats pipes for temperature homogenization: A literature review

Blet

Lips

Sartre

2017

Applied Thermal Engineering

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Heat pipes offer high effective heat transfer in a purely passive way. Other specific properties of heat pipes, like temperature homogenization, can be also reached. In this paper, a literature review is carried out in order to investigate the existing heat pipe systems mainly aiming the reduction of temperature gradients. The review gathering more than sixty references is sorted into various application fields, like thermal management of electronics, of storage vessels or of satellites, for which the management of the temperature uniformity differs by the isothermal surface area, temperature ranges or the targeted precision of the temperature flattening. A summary of heat pipe characteristics for this function of temperature homogenization is then performed to identify their specificities, compared to other applications of heat pipes.

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SMARTS Thermal Architecture for PnPSat-2

Cited by 2 publications

References 1 publication

Enabling Future Spacecraft Missions through Isothermal Bus Thermal Management

Enabling Future Spacecraft Missions through Isothermal Bus Thermal Management

Heats pipes for temperature homogenization: A literature review

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