초록 ▼

A plurality of sufficient closely-packed functional units which are interconnected to form a non-planar payload module assembly 40. Advantageously, the payload modular structure 40 is compact with few piece parts, has low output losses, and is robust enough for supporting complete payloads with or w

A plurality of sufficient closely-packed functional units which are interconnected to form a non-planar payload module assembly 40. Advantageously, the payload modular structure 40 is compact with few piece parts, has low output losses, and is robust enough for supporting complete payloads with or without reflectors. The payload modular structure has utility in various space-based applications as well as in various terrestrial applications.

대표청구항 ▼

1. A payload apparatus for supporting a number of interconnected functional units, said units arranged to provide a sufficient closely-packed modular formation occupying a predetermined volume, said interconnected functional units comprising at least one dissipative element, said apparatus comprisin

1. A payload apparatus for supporting a number of interconnected functional units, said units arranged to provide a sufficient closely-packed modular formation occupying a predetermined volume, said interconnected functional units comprising at least one dissipative element, said apparatus comprising: a non-planar supporting structure for mechanically supporting said interconnected functional units;a number of thermal radiators positioned remotely in relation to the position of the supporting structure; andmeans for defining a thermal pathway between said at least one dissipative element and said number of thermal radiators wherein dissipated heat is transported from said at least one dissipative element to said number of thermal radiators via the thermal pathway, wherein said non-planar supporting structure comprises a faceted tubular body for receiving the units. 2. A payload apparatus as claimed in claim 1, including feed means for converting electrons into photons or vice versa. 3. A payload apparatus as claimed in claim 2, further including functional units mounted at different predetermined locations on a plurality of inner faces of the faceted body and wherein associated feed locations are mounted in proximate relationship to the functional units at different predetermined locations on corresponding external faces of the faceted tubular body. 4. A payload apparatus as claimed in claim 1, further including eight functional units arrayed in an octagon around an opening defined by the faceted body. 5. A payload apparatus as claimed in claim 1 wherein the means for defining a thermal pathway includes temperature compensation means. 6. A payload apparatus as claimed in claim 5 wherein said temperature compensation means includes a number of heat pipes for gathering heat dissipated by the functional units and circuitry responsive to the output of dissipated heat for adjusting temperature differences between the functional units. 7. A spacecraft vehicle or satellite incorporating a payload apparatus as claimed in claim 1. 8. A payload apparatus as claimed in claim 1 wherein the means for defining a thermal pathway includes a number of heat pipes for gathering heat dissipated by the functional units and circuitry responsive to the output of dissipated heat for adjusting temperature differences between the functional units wherein the functional units are mounted to said heat pipes aligned along the tube length on internal faces of the tube. 9. A payload apparatus as claimed in claim 8 wherein heat transfer from the tube mounted heat pipes to the remote radiators is carried out by one of a direct connection and an indirect connection using a fluid loop. 10. A spacecraft vehicle or satellite incorporating a payload apparatus as claimed in claim 1, including thermal radiators facing in the north and south directions and wherein a longitudinal axis of the faceted tube structure is parallel to a north/south axis of the satellite. 11. A spacecraft vehicle or satellite according to claim 10, wherein the means for defining a thermal pathway includes a number of heatpipes for gathering heat dissipated by the functional units and the heatpipes are L-shaped with a longer part of the heatpipe bolted to the banks of functional units within the tube and the other arm of the heatpipe bolted directly to one or other of the north and south radiators. 12. A spacecraft vehicle or satellite according to claim 10, wherein the faceted tubular body includes two separate faceted tubes in which each is structurally supported by a platform of the spacecraft vehicle or satellite so as to be positioned directly on top of one of the north/south facing radiator panels. 13. A spacecraft vehicle or satellite according to claim 10, wherein the payload is distributed in close packed formation across a number of faceted tubes with associated feed being proximately mounted above the tubes. 14. A payload apparatus for supporting a number of interconnected functional units, said units arranged to provide a sufficient closely-packed modular formation occupying a predetermined volume, said interconnected functional units comprising at least one dissipative element, said apparatus comprising: a non-planar supporting structure for mechanically supporting said interconnected functional units;a number of thermal radiators positioned remotely in relation to the position of the supporting structure; andmeans for defining a thermal pathway between said at least one dissipative element and said number of thermal radiators wherein dissipated heat is transported from said at least one dissipative element to said number of thermal radiators via the thermal pathway, said supporting structure comprising a rack-mounting chassis. 15. A payload apparatus as claimed in claim 14 wherein a receiving volume space is defined by the chassis to accommodate a linear array of functional units, each of the units being slidably mounted on the chassis.