Stackable pancake satellite

Patent metadata

Field	Value
Publication number	US-10532830-B2
Application number	US-201615366698-A
Country	US
Kind code	B2
Filing date	Dec 1, 2016
Priority date	Jun 9, 2016
Publication date	Jan 14, 2020
Grant date	Jan 14, 2020

Abstract

A stackable pancake satellite that is configured so that a plurality of the satellites can be stacked within a payload fairing of a launch vehicle. Each satellite includes sections that are folded or rotated together prior to launch, and unfolded or rotated away from each other when deployed. A first section is a satellite body having a first side that acts as a thermal radiator and a second side opposite the first side that includes an antenna. A second section includes one or more solar panels attached adjacent to the first side of the satellite body. A third section includes a splash plate reflector attached adjacent to the second side of the satellite body that reflects signals between Earth and the antenna. When deployed, the solar panels are pointed towards the Sun and the splash plate reflector directs the signals between the Earth and the antenna.

First claim

What is claimed is:

1. A stacked satellite system, comprising:
a plurality of satellites configured for being stacked within a payload fairing of a launch vehicle;
each of the plurality of satellites includes a plurality of sections that are hingedly attached to each other, wherein the plurality of sections are folded or rotated together prior to launch, and the plurality of sections are unfolded or rotated away from each other when deployed upon reaching orbit;
a first one of the plurality of sections is a satellite body having a first side that acts as a thermal radiator and a second side opposite the first side that includes at least one antenna;
a second one of the plurality of sections includes at least one solar panel attached adjacent to the first side of the satellite body, wherein light from the Sun is converted to electricity by the at least one solar panel; and
a third one of the plurality of sections includes at least one splash plate reflector attached adjacent to the second side of the satellite body, wherein radio frequency signals between Earth and the at least one antenna are reflected by the at least one splash plate reflector;
when deployed, the at least one solar panel is rotated away from the first side of the satellite body, so that the at least one solar panel is pointed towards the Sun, and the at least one splash plate reflector is rotated away from the second side of the satellite body to direct the signals between the Earth and the at least one antenna.

2. The system of claim 1 , wherein a periphery outline of the plurality of sections of each satellite when folded together is oval, elliptical, round or polygonal in shape.

3. The system of claim 1 , wherein the plurality of sections of each satellite, when folded together, maintain a substantially flat profile.

4. The system of claim 1 , wherein the satellite body of each satellite has a cavity on the first side and a hollow region on the second side, such that, when folded together, the at least one solar panel of each satellite is folded and stowed within the hollow region, the at least one antenna of each satellite is disposed within the cavity, and the at least one splash plate reflector of each satellite is stored adjacent to the at least one antenna in the cavity.

5. The system of claim 4 , further comprising:
a polygonal closeout member covers the first side of the satellite body of each satellite surrounding the cavity; and
the first side of the satellite body of each satellite that acts as the thermal radiator and the at least one solar panel of each satellite are disposed within the hollow region, and the at least one solar panel of each satellite comprises a plurality of foldable solar arrays that, when folded, are enclosed within the hollow region.

6. The system of claim 4 , wherein the at least one solar panel of each satellite includes a plurality of panel elements having substantially the same shape, and the plurality of panel elements are each folded upon each other to fit within the hollow region.

7. The system of claim 1 , wherein the at least one solar panel of each satellite comprises two or more solar panels.

8. The system of claim 1 , wherein the at least one solar panel of each satellite comprises a multi-segmented array that is configured to be at least partially folded onto itself.

9. The system of claim 1 , wherein the plurality of satellites are disposed within the payload fairing of the launch vehicle in a stacked column configuration prior to launch.

10. The system of claim 1 , wherein the plurality of satellites comprises at least one top satellite disposed vertically on top of at least one bottom satellite within the payload fairing of the launch vehicle, wherein a plurality of corner fittings bear launch loads for both the top and bottom satellites.

11. The system of claim 1 , wherein the plurality of satellites are passively dispensed from the payload fairing of the launch vehicle upon reaching orbit.

12. The system of claim 1 , wherein the first one of the plurality of sections of each satellite includes bus and payload units mounted on or with the first side of the satellite body of each satellite that acts as the thermal radiator.

13. The system of claim 1 , wherein the at least one antenna of each satellite comprises a multi-beam antenna.

14. The system of claim 1 , wherein at least one thruster is attached to the satellite body of each satellite to maintain orbit phasing.

15. The system of claim 1 , wherein the at least one solar panel of each satellite is pointed at the Sun, the at least one splash plate reflector of each satellite is pointed at the Earth, and the first side of the satellite body of each satellite that acts as the thermal radiator is pointed into space.

16. A method for launching a stacked satellite system, comprising:
stacking a plurality of satellites within a payload fairing of a launch vehicle, wherein:
each of the plurality of satellites includes a plurality of sections that are hingedly attached to each other, wherein the plurality of sections are folded or rotated together prior to launch, and the plurality of sections are unfolded or rotated away from each other when deployed upon reaching orbit;
a first one of the plurality of sections is a satellite body having a first side that acts as a thermal radiator and a second side opposite the first side that includes at least one antenna;
a second one of the plurality of sections includes at least one solar panel attached adjacent to the first side of the satellite body, wherein light from the Sun is converted to electricity by the at least one solar panel; and
a third one of the plurality of sections includes at least one splash plate reflector attached adjacent to the second side of the satellite body, wherein radio frequency signals between Earth and the at least one antenna are reflected by the at least one splash plate reflector;

launching the plurality of satellites into orbit using the launch vehicle; and
serially dispensing each oldie plurality of satellites from the payload fairing of the launch vehicle upon reaching orbit, such that, when each of the plurality of satellites is deployed, the second one of the plurality of sections is rotated away from the first side of the satellite body so that the at least one solar panel is pointed towards the Sun, and the third one of the plurality of sections is rotated away from the second side of the satellite body so that the at least one splash plate reflector directs the radio frequency signals between Earth and the at least one antenna.

17. The method of claim 16 , wherein a periphery outline of the plurality of sections of each satellite when folded together is oval, elliptical, round or polygonal in shape.

18. The method of claim 16 , wherein the plurality of sections of each satellite, when folded together, maintain a substantially flat profile.

19. The method of claim 16 , wherein the satellite body of each satellite has a cavity on the first side and a hollow region on the second side, such that, when folded together, the at least one solar panels of each satellite is folded and stowed within the hollow region, the at least one antenna of each satellite is disposed within the cavity, and the at least one splash plate reflector of each satellite is stored adjacent to the at least one antenna in the cavity.

20. The method of claim 19 , wherein:
a polygonal closeout member covers the first side of the satellite body of each satellite surrounding the cavity; and
the fir

Assignees

• Boeing Co

Inventors

• Busche Gregory Clayton

Classifications

• B64G1/10 Primary

  Artificial satellites; Systems of such satellites; Interplanetary vehicles (space shuttles B64G1/14) · CPC title

• B64G1/22

  Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles · CPC title

• B64G1/66

  Arrangements or adaptations of apparatus or instruments, not otherwise provided for · CPC title

• B64G1/44 Primary

  using radiation, e.g. deployable solar arrays · CPC title

• B64G1/503

  Radiator panels · CPC title