Self-contained payload accommodation module

Patent metadata

Field	Value
Publication number	US-11214388-B2
Application number	US-201916243225-A
Country	US
Kind code	B2
Filing date	Jan 9, 2019
Priority date	Jan 9, 2019
Publication date	Jan 4, 2022
Grant date	Jan 4, 2022

Abstract

A self-contained payload module and method of deployment of a payload includes a housing that is configured to engage a propulsive payload adapter hub, at least one deployable payload that is arranged in an interior cavity of the housing and deployable using the propulsive payload adaptor hub, a payload electronics system arranged in the interior cavity, a thermal control system in communication with the at least one payload and arranged in the housing, and at least one antenna that is arranged on the housing and configured for wideband communication.

First claim

What is claimed is:

1. A payload module configured to be arranged in a space vehicle that includes a propulsive payload adapter hub, the propulsive payload adapter hub being releasable from the space vehicle, the payload module comprising:
a housing that is configured to engage the propulsive payload adapter hub for integration of the payload module and the propulsive payload adapter hub;
at least one deployable payload that is arranged in an interior cavity of the housing and deployable from the payload module via a power source of the propulsive payload adapter hub when the payload module and the propulsive payload adapter hub are integrated;
a payload electronics system arranged in the interior cavity;
a thermal control system in communication with the at least one payload and arranged in the housing; and
at least one antenna that is arranged on the housing and configured for wideband communication, the payload module being self-contained via the thermal control system and the at least one antenna being arranged in the payload module, the payload module being self-contained to enable testing of operational characteristics of the payload module prior to integration of the payload module and the propulsive payload adapter hub.

2. The payload module according to claim 1 , wherein the housing and the interior cavity are cylindrical.

3. The payload module according to claim 2 , wherein the at least one payload is arranged within an outer perimeter of the housing and the at least one antenna is mounted to the housing outside the outer perimeter.

4. The payload module according to claim 1 , wherein the at least one payload is cylindrical in shape and has a circular field-of-view.

5. The payload module according to claim 1 , wherein the thermal control system includes a plurality of radiator panels arranged on an outer peripheral surface of the housing.

6. The payload module according to claim 1 further comprising a hub fastener that is configured to connect a perimeter of the housing to the propulsive payload adapter hub.

7. The payload module according to claim 6 , wherein the hub fastener is a ring-shaped clamp band arranged around the perimeter of the housing.

8. The payload module according to claim 6 further comprising a primary vehicle fastener that is arranged on the housing opposite the hub fastener and configured to connect the housing to a primary vehicle opposite the propulsive payload adapter hub.

9. A method of deployment of a payload from a propulsive payload adapter hub, the propulsive payload adapter hub being releasable from a space vehicle, the method comprising:
inserting at least one deployable payload with payload electronics within an interior cavity of a housing of a payload module configured to be arranged in the space vehicle and integrated with the propulsive payload adapter hub;
inserting a thermal control system in the housing and arranging the thermal control system for communication with the at least one payload;
arranging at least one antenna on the housing that is configured for wideband communication;
attaching the housing to the propulsive payload adapter hub; and
deploying the payload using the propulsive payload adapter hub via a power source of the propulsive payload adapter hub when the payload module and the propulsive payload adapter hub are integrated, the payload module being self-contained via the thermal control system and the at least one antenna being arranged in the payload module, the payload module being self-contained to enable testing of operational characteristics of the payload module prior to integration of the payload module and the propulsive payload adapter hub.

10. The method according to claim 9 further comprising arranging the at least one payload to have a circular field-of-view.

11. The method according to claim 9 further comprising testing the payload module for at least one of the operational characteristics before attaching the payload housing to the propulsive payload adapter hub, wherein the operational characteristics include, dynamic, vibration, acoustic, thermal, electromagnetic compatibility, and electromagnetic interference.

12. The method according to claim 11 further comprising attaching the payload module to a primary vehicle.

13. The method according to claim 12 further comprising arranging the payload module, the propulsive payload adapter hub, and the primary vehicle to be coaxially stacked relative to each other.

14. The method according to claim 13 further comprising:
determining a maximum volume available for the payload module based on the a mass and a center of gravity of the primary vehicle and the propulsive payload adapter hub; and
forming the payload module to have a volume that is less than or equal to the maximum volume available.

15. The method according to claim 9 further comprising arranging the at least one payload within an outer perimeter of the housing and mounting the at least one antenna to the housing outside the outer perimeter.

16. The method according to claim 9 further comprising using a mechanical interface to connect a perimeter of the housing to a perimeter of the propulsive payload adapter hub.

17. The method according to claim 9 , wherein inserting the thermal control system in the housing includes arranging a plurality of radiator panels on an outer peripheral surface of the housing.

Assignees

• Raytheon Co

Inventors

• Cosner Christopher M
• Baldwin Michael S

Classifications

• B64G1/643 Primary

  for arranging multiple satellites in a single launcher · CPC title

• B64G1/642

  Clamps, e.g. Marman clamps · CPC title

• B64G1/428

  Power distribution and management · CPC title

• B64G1/503

  Radiator panels · CPC title

• B64G1/641 Primary

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