Spacecraft design with multiple thermal zones
View Patent ↗A spacecraft includes a body, a plurality of separate units, and a first auxiliary radiator panel. The body includes a plurality of sidewalls, at least a first sidewall of the plurality of sidewalls including an outboard-facing radiator surface having optical solar reflectors disposed thereon. A first subset of the plurality of units is thermally coupled with the outboard-facing radiator surface of the first sidewall. A second subset of the plurality of units is thermally coupled with the first auxiliary radiator panel and is isolated from at least conductive thermal heat transfer with the outboard-facing radiator surface of the first sidewall. The first subset of units is spatially proximate to the second subset of units and is configured to operate in a first temperature range. The second subset of units is configured to operate in a second temperature range, the second temperature range being different from the first temperature range.
1. A spacecraft comprising:
a body including a plurality of sidewalls, at least a first sidewall of the plurality of sidewalls including an outboard-facing radiator surface having optical solar reflectors disposed thereon;
a plurality of separate units; and
a first auxiliary radiator panel; wherein
the first auxiliary radiator panel is disposed outboard of the first sidewall;
a first subset of the plurality of units is thermally coupled with the outboard-facing radiator surface of the first sidewall so as to dissipate heat by way of the optical solar reflectors;
a second subset of the plurality of units is thermally coupled with the first auxiliary radiator panel from the outboard-facing radiator surface of the first sidewall;
the first subset of units is spatially proximate to the second subset of units;
the first subset of units is configured to operate in a first temperature range; and
the second subset of units is isolated from at least conductive thermal heat transfer with the outboard-facing radiator surface of the first sidewall and is configured to operate in a second temperature range, the second temperature range being different from the first temperature range.
2. The spacecraft of claim 1 , wherein the plurality of units includes a low noise amplifier (LNA), a traveling-wave tube amplifier (TWTA), an electronic power conditioner (EPC), a channel amplifier (CAMP), and/or an output multiplexer (OMUX).
3. The spacecraft of claim 1 , further comprising a second auxiliary radiator panel; wherein:
a third subset of the plurality of units is thermally coupled with the second auxiliary radiator panel and is isolated from at least conductive thermal heat transfer with the outboard-facing radiator surface of the first sidewall, the third subset of units being configured to operate in a third temperature range,
the second auxiliary radiator panel is isolated from at least conductive thermal heat transfer with the first auxiliary radiator panel, and
the third temperature range is different than the first temperature range.
4. The spacecraft of claim 3 , wherein:
the first temperature range is colder than the second temperature range, and
the third temperature range is hotter than the second temperature range.
5. The spacecraft of claim 1 , further comprising:
multi-layer insulation (Mil) positioned between the outboard-facing radiator surface of the first sidewall and the first auxiliary radiator panel; and
an insulating washer supporting the first auxiliary radiator panel; wherein
the second subset of units is positioned within a cutout of the outboard-facing radiator surface of the first sidewall.
6. The spacecraft of claim 5 , further comprising:
a heat pipe network configured to spread heat across the outboard-facing radiator surface of the first sidewall.
7. The spacecraft of claim 6 , wherein the first auxiliary radiator panel includes an internal heat transfer mechanism including one or both of: embedded heatpipes or spreader heatsinks.
8. An apparatus comprising:
a radiator surface included on an outboard-facing side of a sidewall of a body of a spacecraft and having optical solar reflectors disposed thereon;
a plurality of separate units; and
a first auxiliary radiator panel; wherein
the first auxiliary radiator panel is disposed outboard of the sidewall;
a first subset of the plurality of units is thermally coupled with the radiator surface so as to dissipate heat by way of the optical solar reflectors;
a second subset of the plurality of units is thermally coupled with the first auxiliary radiator panel and is isolated from at least conductive thermal heat transfer with the radiator surface;
the first subset of units is spatially proximate to the second subset of units;
the first subset of units is configured to operate in a first temperature range; and
the second subset of units is configured to operate in a second temperature range, the second temperature range being different from the first temperature range.
9. The apparatus of claim 8 , further comprising:
a third subset of the plurality of units is thermally coupled with a second auxiliary radiator panel and is isolated from at least conductive thermal heat transfer with the radiator surface, the third subset of units being configured to operate in a third temperature range; wherein
the second auxiliary radiator panel is is isolated from at least conductive thermal heat transfer with the first auxiliary radiator panel,
the first temperature range is colder than the second temperature range, and
the third temperature range is hotter than the second temperature range.
10. The apparatus of claim 8 , wherein the plurality of units includes a low noise amplifier (LNA), a traveling-wave tube amplifier (TWTA), an electronic power conditioner (EPC), a channel amplifier (CAMP), and/or an output multiplexer (OMUX).
11. The apparatus of claim 8 , further comprising:
multi-layer insulation (MLI) positioned between the radiator surface configured to be included on the outboard-facing side of the sidewall and the first auxiliary radiator panel; and
an insulating washer supporting the first auxiliary radiator panel; wherein
the second subset of units is positioned within a cutout of the radiator surface.
12. The apparatus of claim 11 , further comprising:
a heat pipe network configured to spread heat across the radiator surface configured to be included on the outboard-facing side of the sidewall.
13. A spacecraft comprising:
a body including a plurality of sidewalls, at least a first sidewall of the plurality of sidewalls including an outboard-facing radiator surface having optical solar reflectors disposed thereon;
a plurality of separate units;
a first auxiliary radiator panel; and
a second auxiliary radiator panel; wherein
the first auxiliary radiator panel is disposed outboard of the first sidewall so as to dissipate heat by way of the optical solar reflectors;
the second auxiliary radiator panel is disposed outboard of the first sidewall;
a first subset of the plurality of units is thermally coupled with the outboard-facing radiator surface of the first sidewall;
a second subset of the plurality of units is thermally coupled with the first auxiliary radiator panel and is isolated from at least conductive thermal heat transfer with the outboard-facing radiator surface of the first sidewall; and
a third subset of the plurality of units is thermally coupled with the second auxiliary radiator panel and is isolated from at least conductive thermal heat transfer with the outboard-facing radiator surface of the first sidewall and from the first auxiliary radiator panel;
the first subset of units is spatially proximate to the second subset of units;
the first subset of units is configured to operate in a first temperature range; and
the second subset of units is configured to operate in a second temperature range, the second temperature range being different from the first temperature range.
14. The spacecraft of claim 13 , wherein:
the third subset of units is configured to operate in a third temperature range;
the first temperature range is colder than the second temperature range; and
the third temperature range is hotter than the second temperature range.
15. The spacecraft of claim 13 , wherein the plurality of units includes a low noise amplifier (LNA), a traveling-wave tube amplifier (TWTA), an electronic power conditioner (EPC), a channel amplifier (CAMP), and/or an output multiplexer (OMUX).
16. The spacecraft of claim 13 , further comprising:
multi-layer insulation (MLI) positioned between the outboard-facing radiator surface of the first sidewall and the first auxiliary radiator panel; and
an insulating washer supporting the first auxiliary radiator panel; wherein
the second subset of units is positioned within a cutout of the outboard-facing radiator surface of the first sidewall.
17. The spacecraft of claim 16 , further comprising:
a heat pipe network configured to spread heat across the outboard-facing radiator surface of the first sidewall.
18. The spacecraft of claim 17 , wherein the first and/or second auxiliary radiator panels includes an internal heat transfer mechanism including one or both of: embedded heatpipes or spreader heatsinks.