Satellite having multiple aspect ratios
View Patent ↗A high capacity satellite having multiple aspect ratios is configured to have at least two modules. Each module includes a first panel and a third panel facing, in an on-orbit configuration, respectively, toward north and south and having a width in an east-west direction (EW width); and a second and a fourth panel oriented, in the on-orbit configuration, respectively, east and west and having a width in the north-south direction (NS width). Each module has a respective aspect ratio of EW width to NS width, a first module is configured with a first aspect ratio, a second module is configured with a second aspect ratio; and the second aspect ratio is substantially larger than the first aspect ratio. At least one antenna reflector is disposed, during launch, proximate to at least one of the first and third panel of the second module.
1. A spacecraft, comprising:
at least two modules, each said module comprising:
a first panel and a third panel substantially facing, in an on-orbit configuration, respectively, toward north and south and having a width in an east-west direction (EW width); and a second and a fourth panel substantially facing, in the on-orbit configuration, respectively, east and west and having a width in the north-south direction (NS width), wherein, whether in the on-orbit configuration or in a launch configuration:
each said module has a respective aspect ratio of EW width to NS width;
a first module is configured with a first aspect ratio;
a second module is configured with a second aspect ratio; and
the second aspect ratio is substantially larger than the first aspect ratio, wherein the second aspect ratio is at least 20% larger than the first aspect ratio.
2. The spacecraft according to claim 1 , further comprising at least one antenna reflector, the antenna reflector having an aperture, wherein the antenna reflector is disposed, in the launch configuration, such that the aperture is proximate to and substantially parallel with one of the first panel and the third panel of the second module.
3. The spacecraft according to claim 2 , wherein the at least one antenna reflector has a major diameter approximately equal to or greater than the EW width of the first panel of the second module.
4. The spacecraft according to claim 2 , wherein the at least one antenna reflector is disposed, in the on-orbit configuration, in an easterly or westerly direction with respect to the at least two modules.
5. The spacecraft according to claim 1 , wherein the first module comprises a launch vehicle mating interface.
6. The spacecraft according to claim 5 , wherein the launch vehicle mating interface is disposed, in the on-orbit configuration, facing the Earth.
7. The spacecraft according to claim 1 , wherein a plurality of thermal radiators are disposed on an external surface of at least one of the first panel and the third panel of at least one of the first module and the second module, and at least one antenna reflector is disposed, in the launch configuration, to cover at least some of the plurality of thermal radiators.
8. The spacecraft according to claim 1 , wherein at least one solar array panel is disposed, during launch, proximate to at least one of the first and third panel of the first module.
9. The spacecraft according to claim 8 , wherein the at least one solar array panel is deployed, in the on-orbit configuration, in a northerly or southerly direction with respect to the at least two modules.
10. The spacecraft according to claim 1 wherein at least two antenna reflectors are disposed, in the launch configuration, proximate to one of the first panel and third panel of the second module.
11. A spacecraft, comprising:
at least two modules, each said module comprising:
a first panel and a third panel substantially facing, in an on-orbit configuration, respectively, toward north and south and having a width in an east-west direction (EW width); and a second and a fourth panel substantially facing, in the on-orbit configuration, respectively, east and west and having a width in the north-south direction (NS width), wherein, whether in the on-orbit configuration or in a launch configuration:
each said module has a respective aspect ratio of EW width to NS width;
a first module is configured with a first aspect ratio;
a second module is configured with a second aspect ratio; and
the first aspect ratio is in the range of approximately 0.8 to 1.2 and the second aspect ratio is at least 1.5.
12. The spacecraft according to claim 11 , wherein the second aspect ratio is at least three.