SPACE VEHICLE WITH CUSTOMIZABLE PAYLOAD AND DOCKING STATION

• US 20150367965A1
• Filed: 06/22/2015
• Published: 12/24/2015
• Est. Priority Date: 06/24/2014
• Status: Active Grant

• Current Assignee: TRIAD National Security, LLC
• Original Assignee: Los Alamos National Security LLC (Government of the United States of America)
• Inventors: Judd, Stephen, Dallmann, Nicholas, McCabe, Kevin, Seitz, Daniel
• Granted Patent: US 9,878,805 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64G 1/10 Artificial satellites; Systems of such satellites; Interplanetary vehicles space shuttles B64G1/14
• CPC Class Codes: B64G 1/222 for deploying structures between a stowed and deployed state
• CPC Class Codes: B64G 1/223 Modular spacecraft systems
• CPC Class Codes: B64G 1/428 Power distribution and management
• CPC Class Codes: B64G 1/44 using radiation, e.g. deployable solar arrays
• CPC Class Codes: B64G 1/641 Interstage or payload connectors docking systems B64G1/646

Abstract

A “black box” space vehicle solution may allow a payload developer to define the mission space and provide mission hardware within a predetermined volume and with predetermined connectivity. Components such as the power module, radios and boards, attitude determination and control system (ADCS), command and data handling (C&DH), etc. may all be provided as part of a “stock” (i.e., core) space vehicle. The payload provided by the payload developer may be plugged into the space vehicle payload section, tested, and launched without custom development of core space vehicle components by the payload developer. A docking station may facilitate convenient development and testing of the space vehicle while reducing handling thereof.

Claims

1. An apparatus, comprising:

a payload section; and

an electrical interface board configured to interface with a payload of the payload section, wherein

the electrical interface board comprises a power and communications interface to a main bus of the apparatus.

2. The apparatus of claim 1, wherein the payload section is external to the apparatus and plugs into the electrical interface board.

3. The apparatus of claim 1, wherein the electrical interface board is customizable to enable specialized payloads and provide interfaces identical to alternative cubesat bus payload standards.

4. The apparatus of claim 1, wherein the electrical interface board interfaces with the main bus of the apparatus such that the payload communicates directly with the electrical interface board and not with other components of the apparatus.

5. The apparatus of claim 1, further comprising:

a power section configured to connect to an interposer board of a docking station.

6. The apparatus of claim 5, wherein the power section comprises connectors for each solar panel, a safe arm connector, and a diagnostic/test connector.

7. The apparatus of claim 1, further comprising:

a digital interface board configured to provide dedicated digital processing for the payload.

8. The apparatus of claim 7, wherein the digital interface board plugs directly into a backplane of the apparatus.

9. The apparatus of claim 7, wherein the digital interface board is fully integrated into a main system of the apparatus, and communicates with the payload section via the electrical interface board.

10. The apparatus of claim 7, wherein the digital interface board inherits a full software stack of the apparatus, comprising a file system, communications, networking, file transfer capabilities, and an ability to be reprogrammed from a ground station.

11. The apparatus of claim 1, wherein the payload is developed via a payload development kit comprising a mechanical portion, an electrical portion, a fit-check enclosure, and a space vehicle simulator.

12. The apparatus of claim 11, wherein the mechanical portion comprises an empty shell.

13. The apparatus of claim 11, wherein the electrical portion comprises a payload module circuit board that interfaces the payload to the apparatus.

14. The apparatus of claim 11, wherein the fit-check enclosure ensures that a final payload will interface mechanically to the apparatus and fit in a dispenser, and the space vehicle simulator ensures that the payload section will interface electrically and software-wise to the apparatus.

15. The apparatus of claim 1, wherein the electrical interface board provides a common power and communications interface to the payload section, comprising bi-directional serial communications, bi-directional parallel input/output (I/O) lines, interrupts, a reset line, and a plurality of common voltages.

16. A space vehicle, comprising:

a payload;

a payload section configured to house the payload;

an electrical interface board configured to interface with the payload; and

a digital interface board configured to provide dedicated digital processing for the payload, wherein

the electrical interface board comprises a power and communications interface to a main bus of the space vehicle, and

the digital interface board communicates with the payload section via the payload electrical interface board and inherits a software stack of the space vehicle.

17. The space vehicle of claim 16, wherein the digital interface board inherits a full software stack of the space vehicle, comprising a file system, communications, networking, file transfer capabilities, and an ability to be reprogrammed from a ground station.

18. The space vehicle of claim 16, wherein the electrical interface board provides a common power and communications interface to the payload section, comprising bi-directional serial communications, bi-directional parallel input/output (I/O) lines, interrupts, a reset line, and a plurality of common voltages.

19. The space vehicle of claim 16, further comprising:

a power section configured to connect to an interposer board of a docking station;

wherein the power section comprises connectors for each solar panel, a safe arm connector, and a diagnostic/test connector.

20. A payload development kit, comprising:

a mechanical portion comprising an empty shell;

an electrical portion comprising a payload module circuit board that interfaces a payload to a remainder of a space vehicle;

a fit-check enclosure that ensures that a final payload will interface mechanically to the space vehicle and fit in a dispenser; and

a space vehicle simulator that ensures that the payload section will interface electrically and software-wise to the space vehicle.