Spacecraft systems and methods

Patent metadata

Field	Value
Publication number	US-11891196-B2
Application number	US-202117308433-A
Country	US
Kind code	B2
Filing date	May 5, 2021
Priority date	May 6, 2020
Publication date	Feb 6, 2024
Grant date	Feb 6, 2024

Abstract

Systems and methods for configuring, packaging, and deploying spacecraft are provided. More particularly, spacecraft are configured with statically mounted instruments. An end of the spacecraft to which the instruments are mounted is relatively distant from a spacecraft bus, and has a narrow width relative to the spacecraft bus. During launch multiple overlapping and interleaved spacecraft are disposed radially about a longitudinal axis of the launch vehicle.

First claim

What is claimed is:

1. A spacecraft system, comprising:
a launch vehicle, the launch vehicle including first and second mounting rings located along a longitudinal axis of the launch vehicle;
a first spacecraft having first and second ends, wherein the first spacecraft is connected to the first mounting ring, wherein the first end of the first spacecraft is adjacent the second mounting ring, wherein a first plane that is perpendicular to the longitudinal axis of the launch vehicle is coincident with the first end of the first spacecraft and intersects the second mounting ring, wherein the second end of the first spacecraft is adjacent the first mounting ring, and wherein a second plane that is perpendicular to the longitudinal axis of the launch vehicle is coincident with the second end of the first spacecraft and intersects the first mounting ring; and
a second spacecraft having first and second ends, wherein the second spacecraft is connected to the second mounting ring, wherein the first end of the second spacecraft is adjacent the first mounting ring, wherein a third plane that is perpendicular to the longitudinal axis of the launch vehicle is coincident with the first end of the second spacecraft and intersects the first mounting ring, wherein the second end of the second spacecraft is adjacent the second mounting ring, and wherein a fourth plane that is perpendicular to the longitudinal axis of the launch vehicle is coincident with the second end of the second spacecraft and intersects the second mounting ring.

2. The spacecraft system of claim 1 , wherein the launch vehicle further includes a platform, and wherein the first mounting ring is connected to the platform.

3. A spacecraft system, comprising:
a launch vehicle, the launch vehicle including first and second mounting rings located along a longitudinal axis of the launch vehicle;
a first spacecraft having first and second ends, wherein the first spacecraft is connected to the first mounting ring, wherein the first end of the first spacecraft is adjacent the second mounting ring, wherein a first plane that is perpendicular to the longitudinal axis of the launch vehicle is coincident with the first end of the first spacecraft and intersects the second mounting ring, and wherein the second end of the first spacecraft is adjacent the first mounting ring; and
a second spacecraft having first and second ends, wherein the second spacecraft is connected to the second mounting ring, wherein the first end of the second spacecraft is adjacent the first mounting ring, wherein a second plane that is perpendicular to the longitudinal axis of the launch vehicle is coincident with the first end of the second spacecraft and intersects the first mounting ring, wherein the second end of the second spacecraft is adjacent the second mounting ring, and wherein the second mounting ring is directly connected to the first mounting ring.

4. The spacecraft system of claim 2 , wherein the second mounting ring is connected to the first mounting ring via at least a first spacer element.

5. The spacecraft system of claim 1 , wherein the first spacecraft is included in a first plurality of spacecraft that are all connected to and radially disposed about the first mounting ring, and wherein the second spacecraft is included in a second plurality of spacecraft that are all connected to and radially disposed about the second mounting ring.

6. The spacecraft system of claim 5 , wherein each spacecraft in the first plurality of spacecraft is adjacent to at least one spacecraft in the second plurality of spacecraft.

7. The spacecraft system of claim 6 , wherein a spacecraft bus portion of each of the spacecraft in the first plurality of spacecraft is connected to the first mounting ring via a corresponding radial fixture, and wherein a spacecraft bus portion of each of the spacecraft in the second plurality of spacecraft is connected to the second mounting ring via a corresponding radial fixture.

8. The spacecraft system of claim 7 , wherein the first end of each of the spacecraft includes at least one instrument.

9. The spacecraft system of claim 8 , wherein for each spacecraft the first end of the spacecraft is fixed relative to the second end of the spacecraft by a spacer member.

10. The spacecraft system of claim 1 , wherein a first width dimension of the first spacecraft along a first direction perpendicular to the longitudinal axis of the launch vehicle and proximate to the first end of the first spacecraft is less than a second width dimension of the first spacecraft taken along the first direction and proximate to the second end of the first spacecraft.

11. A method for deploying a spacecraft, comprising:
providing a first spacecraft having a bus portion and a first end portion, wherein the first spacecraft includes a power component in the bus portion and a sensor component in the first end portion, and wherein the bus portion is wider than the first end portion;
providing a second spacecraft having a bus portion and a first end portion, wherein the second spacecraft includes a power component in the bus portion and a sensor component in the first end portion, and wherein the bus portion is wider than the first end portion;
mounting the bus portion of the first spacecraft to a first mounting ring of a launch vehicle; and
mounting the bus portion of the second spacecraft to a second mounting ring of the launch vehicle, wherein the first and second mounting rings are stacked on top of one another along a longitudinal axis of the launch vehicle, wherein the first spacecraft has first and second ends, wherein a first plane that is perpendicular to a longitudinal axis of the launch vehicle is coincident with the first end of the first spacecraft and intersects the second mounting ring, wherein the second spacecraft has first and second ends, and wherein a second plane that is perpendicular to the longitudinal axis of the launch vehicle is coincident with the first end of the second spacecraft and intersects the first mounting ring.

12. The method of claim 11 , further comprising:
launching the launch vehicle;
deploying the first spacecraft into orbit about the Earth, wherein a location of the first end portion of the first spacecraft relative to the bus portion of the first spacecraft while launching the launch vehicle is the same as after deploying the first spacecraft into orbit about the Earth; and
operating the sensor component, wherein the sensor component has a field of view that extends in multiple directions relative to the first spacecraft.

13. The method of claim 11 , further comprising:
wherein the first spacecraft is part of a first plurality of spacecraft, wherein each spacecraft in the first plurality of spacecraft includes a bus portion and a first end portion, wherein each spacecraft in the first plurality of spacecraft includes a power component in the bus portion and a sensor component in the first end portion, and wherein the bus portion is wider than the first end portion;
wherein the second spacecraft is part of a second plurality of spacecraft, wherein each spacecraft in the second plurality of spacecraft includes a bus portion and a first end portion, wherein the second spacecraft includes a power component in the bus portion and a sensor component in the first end portion, and wherein the bus portion is wider than the first end portion;
mounting the bus portion of each spacecraft in the first plurality of spacecraft to the first mounting ring of the launch vehicle, wherein the first end portion of each spacecraft in the first plurality of spacecraft is nearer a nose cone of the launch vehicle than the

Assignees

• Ball Aerospace & Tech Corp

Inventors

• York Adam
• Juarez Corey

Classifications

• B64G1/1085 Primary

  Swarms and constellations · CPC title

• B64G1/643 Primary

  for arranging multiple satellites in a single launcher · CPC title

• B64G1/002

  Launch systems · CPC title

• B64G1/641 Primary

  Interstage or payload connectors (docking systems B64G1/646) · CPC title

• B64G1/443

  Photovoltaic cell arrays · CPC title