Estimating the thermally induced acceleration of the New Horizons spacecraft

Guerra, André G. C.; Francisco, Frederico; Gil, P. J. S.; Bertolami, Orfeu

doi:10.1103/physrevd.95.124027

Cited by 2 publications

(1 citation statement)

References 15 publications

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“…The software has its own advantages, including having standard electronic packages, the easiness to add connections between components, or even the automatic view factor computation, for instance. Nevertheless, there are alternative methods, like the lumped-parameter representation [6], or others that have been used on the Pioneer, Cassini and New Horizon probes, for estimating the residual accelerations generated by the spacecraft thermal emissions [8,9,10].…”

Section: Introductionmentioning

confidence: 99%

Thermal analysis of the electronics of a CubeSat mission

Guerra,

Nodar-López,

Tubó-Pardavila

2018

Preprint

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CubeSat satellites are small cube-shaped space platforms that are very popular among academic, research and start-up communities mostly due to their reduced mission costs and short development time. This comes with an easy access to space, which enables high risk missions that would not be feasible otherwise. Thus, most of the subsystems available for these satellites have been adapted to a rather fast development methodology. However, thermal control engineering is still somewhat overlooked due to its complexity and long-term development characteristics. Moreover, since CubeSat projects often rely in commercial off-the-shelf components, it is necessary to understand their necessities in terms of thermal control. The main reason for this is because these components are not originally designed to operate in the space environment, and may degrade faster when operated either under too hot or too cold conditions. In this context, this article presents the results of several thermal analyses and tests conducted over power amplifiers and field-programmable gate array devices, commonly used in CubeSat subsystems and payloads. Passive thermal control methods, mostly based on thermal straps, are explored as potential thermal control solutions due to their low cost and development constraints.

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Section: Introductionmentioning

confidence: 99%

Thermal analysis of the electronics of a CubeSat mission

Guerra,

Nodar-López,

Tubó-Pardavila

2018

Preprint

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When leaving the Solar system: Dark matter makes a difference

Belbruno

Green²

2022

Monthly Notices of the Royal Astronomical Society

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A resultant gravitational force due to the current estimates of the virial mass of the Milky Way galaxy, dominated by dark matter, is estimated near the Sun and is described in two different analytical models yielding consistent results. One is a two step Hernquist model, the other is a Navarro-Frenk-White model. The effect of this force is estimated on trajectories for spacecraft sufficiently far from the Sun. The difficulty of detecting this force is studied. It is concluded that its effect should be considered for certain spacecraft missions. Its effect on the Pioneer and New Horizons spacecrafts is discussed. A future mission is discussed that may be able to detect this force. Implications of this force are discussed with its impact for problems in planetary astronomy and astrophysics.

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Estimating the thermally induced acceleration of the New Horizons spacecraft

Cited by 2 publications

References 15 publications

Thermal analysis of the electronics of a CubeSat mission

Thermal analysis of the electronics of a CubeSat mission

When leaving the Solar system: Dark matter makes a difference

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