Dispenserless multi-satellite launch configuration with simple adapter interface

Patent metadata

Field	Value
Publication number	US-12017808-B2
Application number	US-202117554000-A
Country	US
Kind code	B2
Filing date	Dec 17, 2021
Priority date	Dec 17, 2021
Publication date	Jun 25, 2024
Grant date	Jun 25, 2024

Abstract

Technology is disclosed for a dispenserless multi-satellite launch configuration in which multiple satellites are interconnected to form a composite beam structure that provides stability independently of the launch vehicle. When in the launch configuration, the satellites are formed into a bundle, where each satellite connects by one or more simple connector along the edges of its inner facing vertical side to the satellite adjacent on each side. This composite beam structure provides a stable launch configuration independently of the launch vehicle. Each of the satellites also has one or more connectors along the bottom edge of the inner facing vertical side allowing the bundle to be attached to a ring type launch vehicle interface. Once launched, the satellites can be dispensed by releasing the connector.

First claim

What is claimed is:

1. A system, comprising:
a plurality of N satellites, each having a stowed configuration and a deployed configuration, the plurality of satellites configured to connect together into a launch configuration, each of the satellites comprising:
one or more first connectors configured to connect to an interface of a launch vehicle, the one or more first connectors on a bottom side of the satellite when in the launch configuration; and
one or more pairs of second connectors on vertical sides of the satellite, a first of each of the pair of second connectors configured to connect to another of the satellites to a first side of the satellite when in the launch configuration and a second of each of the pair of second connectors configured to connect to another of the satellites to a second side of the satellite when in the launch configuration, and

a first plurality of the satellites each further comprising a corresponding stowable appendage,
the plurality of satellites, when in the stowed configuration, configured to connect to each other by the second connectors to form the launch configuration as a composite bundle structure independent of the launch vehicle that is configured to connect to the launch vehicle interface by the first connectors, and
when, in the launch configuration, the corresponding stowable appendages of each of the first plurality of the satellites are stowed one above another above all of the plurality of satellites of the composite bundle structure.

2. The system of claim 1 , further comprising:
the launch vehicle, comprising:
an interface configured to connect to the first connectors of the plurality of satellites in the launch configuration.

3. The system of claim 2 , wherein the interface is a ring structure configured to connect to the first connectors of the plurality of satellites in the launch configuration.

4. The system of claim 3 , wherein the launch vehicle further comprises:
a fairing covering the plurality of satellites in the launch configuration.

5. The system of claim 1 , wherein each of the satellites comprise a truss-type frame structure.

6. The system of claim 1 , wherein:
each of the satellites includes a first rectangular side, wherein, when the satellites are in the launch configuration, the first rectangular sides are inward facing vertical sides, and
for each of the satellites:
the one or more first connectors are located along a lower edge of the first rectangular side, and
a first of each of the one or more pairs of second connectors are located on a first vertical edge of the first rectangular side and a second of each of the one or more pairs of second connectors are located on a second vertical edge of the first rectangular side.

7. The system of claim 1 , wherein the corresponding stowable appendage of the first of the satellites is a reflector.

8. A method, comprising:
receiving a plurality of N satellites, a first plurality of the plurality of satellites each including a stowable appendage;
forming the satellites into a launch configuration, including:
connecting each of the satellites to a first other one of the satellites along one side and to a second other one of the satellites along another side to form a bundle of the satellites; and
subsequent to forming the bundle of the satellites, stowing the stowable appendages of each of the first plurality of the satellites one above another above all of the plurality of satellites of the bundle of the satellites; and

attaching the bundle of the satellites in the launch configuration to a launch vehicle by attaching each of the satellites by one or more connectors on the bottom thereof, but not connecting the satellites along the sides thereof to the launch vehicle.

9. The method of claim 8 , wherein the satellites are formed into the bundle prior to connecting the bundle to the launch vehicle.

10. The method of claim 8 , wherein one or more of the satellites are attached to the launch vehicle prior to forming the satellites into the bundle.

11. The method of claim 8 , further comprising:
subsequent to attaching the bundle of the satellites in the launch configuration to a launch vehicle, covering the bundle with a fairing of the launch vehicle.

12. The method of claim 8 , wherein
connecting each of the satellites to the first other one of the satellites along the one side includes attaching one or more connectors along the one side; and
connecting each of the satellites to the second other one of the satellites along the another side includes attaching one or more connectors along the another side.

13. The method of claim 8 , wherein receiving the plurality of satellites includes putting each of the satellites into a stowed configuration prior to forming the satellites into a launch configuration.

14. A satellite, comprising:
a frame structure having a first rectangular side;
one or more interface connectors located along a lower edge of the first rectangular side and configured to connect to an interface of a launch vehicle;
one or more first connectors located on a first vertical edge of the first rectangular side and configured to connect to a first of a plurality of additional satellites;
one or more second connectors located on a second vertical edge of the first rectangular side and configured to connect to a second of the plurality of additional satellites, the one or more first connectors and the one or more second connectors configured to connect the satellite and the plurality of additional satellites to form a launch configuration as a composite bundle that is configured to connect to the interface of the launch vehicle by the one or more interface connectors; and
a stowable appendage, wherein, when in the launch configuration, the stowable appendage is stowed above the bundle, including being stowed above the satellite and above each of the additional satellites of the composite bundle and above a stowable appendage of each of one or more of the additional satellites.

15. The system of claim 1 , wherein each of the second connectors comprises one of either a cup or a cone configured to connect the other of the cup or the cone as a cup and cone pair when in the launch configuration, the cup and cone pair configured as a passive spring mechanism that, when released from the launch configuration, is configured to deploy the satellites.

16. The system of claim 1 , wherein each of the satellites further comprises:
a pair of solar arrays each mounted on a corresponding one of a first pair of opposing sides of the satellite and configured to fold into a deployable stowed configuration; and
one or both of a reflector and an antenna mounted on each of one of a second pair of opposing sides of the satellite and configured to fold into a deployable stowed configuration.

17. The method of claim 8 , wherein an additional one or more of the plurality of satellites further comprise a corresponding stowable appendage and forming the satellites into the launch configuration further includes:
stowing the corresponding stowable appendages of the first of the satellites and the corresponding stowable appendages of the additional one or more satellites one above another above the plurality of the bundle of satellites.

18. The method of claim 12 , wherein each of the connectors along the one side comprise a cup and each of the connectors along the other side comprise a cone, and wherein:
connecting each of the satellites to the first other one of the satellites along the one side includes attaching the cups alo

Assignees

• Maxar Space Llc

Inventors

• Freestone Michael
• Boccio Joel

Classifications

• B64G1/641 Primary

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

• B64G1/643

  for arranging multiple satellites in a single launcher · CPC title

• B64G1/642

  Clamps, e.g. Marman clamps · CPC title

• B64G1/002

  Launch systems · CPC title

• B64G1/10

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