초록 ▼

A spacecraft, along with a spacecraft radiator system and spacecraft heat dissipation method are disclosed. The spacecraft comprises a body, a plurality of solar arrays, and the spacecraft radiator system. The spacecraft radiator system comprises first and second opposite facing payload radiators, f

A spacecraft, along with a spacecraft radiator system and spacecraft heat dissipation method are disclosed. The spacecraft comprises a body, a plurality of solar arrays, and the spacecraft radiator system. The spacecraft radiator system comprises first and second opposite facing payload radiators, first and second opposite facing deployable radiators, and one or more coupling or loop heat pipes cross coupling opposite facing payload and deployable radiators so that they function in tandem. By cross-coupling the opposite facing payload and deployable radiators, one of the two radiators acting in tandem is always in the shade during solstice seasons. Consequently, the solar load processed by the radiator system is minimized, thereby, increasing the thermal dissipation capability of the radiator system by approximately 15%.

대표청구항 ▼

1. A spacecraft radiator system for use on a spacecraft having a body and a plurality of solar arrays, the system comprising:first and second opposite facing payload radiators; first and second opposite facing deployable radiators; and one or more coupling heat pipes that cross couple opposite facin

1. A spacecraft radiator system for use on a spacecraft having a body and a plurality of solar arrays, the system comprising:first and second opposite facing payload radiators; first and second opposite facing deployable radiators; and one or more coupling heat pipes that cross couple opposite facing payload and deployable radiators. 2. The spacecraft radiator system recited in claim 1 wherein the one or more coupling heat pipes comprise loop heat pipes.3. A spacecraft comprising:a body; a plurality of solar arrays; a spacecraft radiator system comprising: first and second opposite facing payload radiators; first and second opposite facing deployable radiators; and one or more coupling heat pities that cross couple opposite facing payload and deployable radiators. 4. The spacecraft recited in claim 3 wherein the one or more coupling heat pipes comprise loop heat pipes.5. A spacecraft heat dissipation method comprising the steps of:configuring a spacecraft to have a body, a plurality of solar arrays, first and second opposite facing payload radiators, first and second opposite facing deployable radiators, and loop heat pipes cross coupling opposite facing payload and deployable radiators; launching the spacecraft into orbit; and when in orbit cross coupling heat coupled to a respective payload radiators to an opposite facing deployable radiator.