SmallSat platform with standard interfaces

Patent metadata

Field	Value
Publication number	US-11208217-B1
Application number	US-202016835366-A
Country	US
Kind code	B1
Filing date	Mar 31, 2020
Priority date	Apr 8, 2019
Publication date	Dec 28, 2021
Grant date	Dec 28, 2021

Abstract

In at least one aspect, a small satellite includes a cylindrical body, a predetermined payload volume, a payload adapter ring mechanical interface for interchangeably mechanically coupling to a launch vehicle payload adapter ring, an electrical interface specifying a set of electrical specifications for interchangeably electrically coupling to the launch vehicle payload adapter ring, a specified center of gravity location and specified frequency response, where the predetermined payload volume, payload adapter ring mechanical interface, electrical interface, specified center of gravity location, and frequency response range allow the small satellite to be interchanged with other small satellites when coupling to the launch vehicle.

First claim

What is claimed is:

1. A small satellite comprising:
a cylindrical body;
a predetermined payload volume;
a payload adapter ring mechanical interface for interchangeably mechanically coupling to a launch vehicle payload adapter ring;
an electrical interface specifying a set of electrical specifications for interchangeably electrically coupling to the launch vehicle payload adapter ring;
a specified center of gravity location and specified mechanical frequency response;
wherein the predetermined payload volume, payload adapter ring mechanical interface, electrical interface, specified center of gravity location, and mechanical frequency response range allow the small satellite to be interchanged with other small satellites when coupling to the launch vehicle.

2. The small satellite of claim 1 , wherein a diameter of the cylindrical body is larger than a height.

3. The small satellite of claim 2 , wherein the payload volume is approximately 392 U, where a U is 10 cm 3 .

4. The small satellite of claim 2 , wherein the launch vehicle payload adapter ring is an Evolved Expendable Launch Vehicle Secondary Payload Adaptor Grande ring.

5. The small satellite of claim 2 , configured to hold a payload of approximately 100 kg and approximately 100 W.

6. The small satellite of claim 1 , wherein a height of the cylindrical body is larger than a diameter.

7. The small satellite of claim 5 , wherein the payload volume is approximately 53 U, where a U is 10 cm 3 .

8. The small satellite of claim 5 , wherein the launch vehicle payload adapter ring is a standard Evolved Expendable Launch Vehicle Secondary Payload Adaptor ring.

9. The small satellite of claim 5 , configured to hold a payload of approximately 17.5 kg and approximately 20 W.

10. The small satellite of claim 1 , wherein the specified mechanical frequency response is approximately 88 Hz.

11. A method of providing a small satellite comprising:
constructing a cylindrical body to enclose a predetermined payload volume;
attaching a payload adapter ring mechanical interface to the cylindrical body for interchangeably mechanically coupling to a launch vehicle payload adapter ring;
providing an electrical interface complying with a set of electrical specifications for interchangeably electrically coupling to the launch vehicle payload adapter ring;
weighting the small satellite to achieve a specified center of gravity location and specified frequency response;
utilizing the predetermined payload volume, payload adapter ring mechanical interface, electrical interface, specified center of gravity location, and frequency response range to interchange the small satellite with other small satellites when coupling to the launch vehicle.

12. The method of claim 11 , wherein a diameter of the cylindrical body is larger than a height.

13. The method of claim 12 , wherein the payload volume is approximately 392 U, where a U is 10 cm 3 .

14. The method of claim 12 , wherein the launch vehicle payload adapter ring is an Evolved Expendable Launch Vehicle Secondary Payload Adaptor Grande ring.

15. The method of claim 12 , comprising configuring the cylindrical body to hold a payload of approximately 100 kg and approximately 100 W.

16. The method of claim 11 , wherein a height of the cylindrical body is larger than a diameter.

17. The method of claim 16 , wherein the payload volume is approximately 53 U, where a U is 10 cm 3 .

18. The method of claim 16 , wherein the launch vehicle payload adapter ring is a standard Evolved Expendable Launch Vehicle Secondary Payload Adaptor ring.

19. The method of claim 16 , comprising configuring the cylindrical body to hold a payload of approximately 17.5 kg and approximately 20 W.

20. The method of claim 11 , wherein the specified frequency response is approximately 88 Hz.

Assignees

• Nasa

Inventors

• Valinia Azita
• Burt Irving
• Pham Bruce
• Ganel Opher

Classifications

• B64G1/644

  arranged for independent deployment · CPC title

• B64G1/428

  Power distribution and management · CPC title

• B64G1/642

  Clamps, e.g. Marman clamps · CPC title

• B64G1/10 Primary

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

• B64G1/641

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