Satellite dispenser and method of supporting a plurality of satellites

1. A satellite dispenser, comprising:

a central tubular structure;

a plurality of satellites arranged around the central tubular structure; and

a plurality of shear connectors coupling the central tubular structure and the plurality of satellites together in shear continuity, each one of the plurality of shear connectors comprising:

a connector first portion coupled to the central tubular structure;

a connector second portion coupled to one of the plurality of satellites;

a shear pin that couples the connector first portion and the connector second portion together in shear; and

a releasable fastener that couples the connector first portion and the connector second portion together and that is configured to selectively separate the connector second portion from the connector first portion in response to a command signal,

wherein:

the connector first portion comprises a first aperture;

the connector second portion comprises a second aperture;

the shear pin comprises a pin first portion having a cylindrical surface and a pin second portion having a frustoconical surface;

a largest diameter of the frustoconical surface is greater than a diameter of the cylindrical surface;

the pin first portion is received by one of the first aperture or the second aperture; and

the pin second portion is received by another one of the first aperture or the second aperture.

2. The satellite dispenser of claim 1 , wherein the connector first portion and the connector second portion each one of the plurality of shear connectors is separable to selectively release the plurality of satellites from the central tubular structure.

3. The satellite dispenser of claim 1 , wherein:

the central tubular structure comprises a plurality of frame members and a skin, coupled to the plurality of frame members; and

each one of the plurality of shear connectors couples one of the plurality of satellites to one of the plurality of frame members.

4. The satellite dispenser of claim 3 , wherein:

each one of the plurality of satellites comprises a plurality of bulkheads; and

each one of the plurality of shear connectors couples one of the plurality of bulkheads to one of the plurality of frame members.

5. The satellite dispenser of claim 4 , wherein:

the connector first portion is coupled to one of the plurality of frame members;

the connector second portion is coupled to one of the plurality of bulkheads; and

the connector second portion is selectively separable from the connector first portion along a plane of separation.

6. The satellite dispenser of claim 1 , wherein:

the connector first portion comprises a plurality of first apertures;

the connector second portion comprises a plurality of second apertures; and

each one of the plurality of shear connectors comprises a plurality of shear pins;

the pin first portion of each one of the plurality of shear pins is received by one of the plurality of first apertures; and

the pin second portion of each one of the plurality of shear pins is received by one of the plurality of second apertures.

7. The satellite dispenser of claim 1 , wherein:

the pin first portion of the shear pin is received by the one of the first aperture or the second aperture via a transition fit or an interference fit; and

the pin second portion of the shear pin is received by the another one of the first aperture or the second aperture via a transition fit or an interference fit.

8. The satellite dispenser of claim 4 , wherein sets of the plurality of shear connectors couple each one of the plurality of bulkheads to a corresponding one of the plurality of frame members.

9. The satellite dispenser of claim 8 , wherein:

the plurality of bulkheads of each one of the plurality of satellites comprises:

a first closeout bulkhead;

a second closeout bulkhead, opposite to the first closeout bulkhead; and

an interior bulkhead located between the first closeout bulkhead and the second closeout bulkhead; and

a first one of the sets of the plurality of shear connectors couples the first closeout bulkhead to a first one of the plurality of frame members;

a second one of the sets of the plurality of shear connectors couples the second closeout bulkhead to a second one of the plurality of frame members; and

a third one of the sets of the plurality of shear connectors couples the interior bulkhead to a third one of the plurality of frame members.

10. The satellite dispenser of claim 3 , wherein the plurality of frame members is located on an interior of the central tubular structure.

11. The satellite dispenser of claim 1 , further comprising a fitting coupled to the central tubular structure, wherein the fitting is configured to interface with a launch vehicle.

12. A spacecraft, comprising:

a launch vehicle; and

a satellite dispenser coupled to the launch vehicle, wherein the satellite dispenser comprises:

a central tubular structure;

a plurality of satellites arranged around the central tubular structure; and

a plurality of shear connectors coupling the central tubular structure and the plurality of satellites together in shear continuity, each one of the plurality of shear connectors comprising:

a connector first portion coupled to the central tubular structure;

a connector second portion coupled to one of the plurality of satellites;

a shear pin that couples the connector first portion and the connector second portion together in shear; and

a releasable fastener that couples the connector first portion and the connector second portion together and that is configured to selectively separate the connector second portion from the connector first portion in response to a command,

wherein:

the connector first portion comprises a first aperture;

the connector second portion comprises a second aperture;

the shear pin comprises a pin first portion having a cylindrical surface and a pin second portion having a frustoconical surface;

a largest diameter of the frustoconical surface is greater than a diameter of the cylindrical surface;

the pin first portion is received by one of the first aperture or the second aperture;

the pin second portion is received by another one of the first aperture or the second aperture

the connector first portion and the connector second portion of each one of the plurality of shear connectors is separable to selectively release the plurality of satellites from the central tubular structure.

13. The spacecraft of claim 12 , wherein:

the central tubular structure has a longitudinal axis and comprises:

a plurality of frame members extending along the longitudinal axis; and

a skin coupled to the plurality of frame members;

each one of the plurality of satellites comprises:

a plurality of bulkheads; and

an external shell, coupled to the plurality of bulkheads; and

each one of the plurality of shear connectors couples one of the plurality of bulkheads to one of the plurality of frame members.

14. The spacecraft of claim 13 , wherein a set of the plurality of shear connectors couples each one of the plurality of bulkheads to a corresponding one of the plurality of frame members.

15. The spacecraft of claim 13 , wherein:

the connector first portion is coupled to one of the plurality of frame members; and

the connector second portion is coupled to one of the plurality of bulkheads; and

the connector second portion is selectively separable from the connector first portion along a plane of separation.

16. A method of supporting a plurality of satellites, the method comprising steps of:

arranging the plurality of satellites around a central tubular structure; and

releasably coupling each one of the plurality of satellites and the central tubular structure together in shear continuity using a plurality of shear connectors,

wherein:

each one of the plurality of shear connectors comprises:

a connector first portion coupled to the central tubular structure;

a connector second portion coupled to one of the plurality of satellites;

a shear pin that couples the connector first portion and the connector second portion together in shear; and

a releasable fastener that couples the connector first portion and the connector second portion together and that is configured to selectively separate the connector second portion from the connector first portion in response to a command signal;

the connector first portion comprises a first aperture;

the connector second portion comprises a second aperture;

the shear pin comprises a pin first portion having a cylindrical surface and a pin second portion having a frustoconical surface;

a largest diameter of the frustoconical surface is greater than a diameter of the cylindrical surface;

the pin first portion is received by one of the first aperture or the second aperture;

the pin second portion is received by another one of the first aperture or the second aperture; and

the connector first portion and the connector second portion of each one of the plurality of shear connectors is separable to selectively release the plurality of satellites from the central tubular structure.

17. The method of claim 16 , wherein the step of releasably coupling each one of the plurality of satellites and the central tubular structure together in shear continuity using the plurality of shear connectors comprises:

coupling the connector second portion to at least one of a plurality of bulkheads of each one of the plurality of satellites;

coupling the connector first portion to at least one of a plurality of frame members of the central tubular structure; and

coupling the connector second portion to the connector first portion using a plurality of shear pins.

18. The method of claim 16 , further comprising selectively separating the connector second portion from the connector first portion of each one of the plurality of shear connectors along a center axis of the shear pin to release each one of the plurality of satellites from the central tubular structure.

19. The satellite dispenser of claim 1 , wherein the releasable fastener is configured to react to at least one of an axial load, a bending load, and a torsion load acting along a center axis of at least one of the plurality of shear connectors.

20. The spacecraft of claim 12 , wherein the releasable fastener is configured to react to at least one of an axial load, a bending load, and a torsion load acting along a center axis of at least one of the plurality of shear connectors.