Integrated navigation and communication system for use in distributed spacecraft systems

• US 6,721,658 B2
• Filed: 06/14/2002
• Issued: 04/13/2004
• Est. Priority Date: 06/14/2001
• Status: Active Grant

• Current Assignee: Johns Hopkins University
• Original Assignee: Johns Hopkins University
• Inventors: Devereux, William S., Stadter, Patrick A.
• Primary Examiner(s): Black, Thomas G.
• Assistant Examiner(s): MANCHO, RONNIE M
• Application Number:
  US10/172,018
• Publication Number:
  US 20020190163A1
• Time in Patent Office: 669 Days
• Field of Search: 701/200, 701/213, 701/215, 342/357.12, 342/357.13, 342/357.06, 439/608, 439/620, 439/485, 439/487, 439/94, 455/427, 455/13.2, 361/709, 361/704, 361/720, 709/238, 709/227, 709/217, 716/16, 174/35.R, 174/35.C, 174/252, 244/176, 370/281, 370/282, 370/280, 370/277
• US Class Current: 701/213
• CPC Class Codes: B64G 1/1085 Swarms and constellations
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors

Abstract

An integrated navigation and communication system that enables distributed spacecraft system operations. The system is a modular, extensible system that supports science operations among multiple, distributed spacecraft by implementing the essential functions of navigation, communication and control. Distributed spacecraft systems, also called formation flying systems, extend the capabilities of single-spacecraft missions by providing a platform for complex sensing tasks, including multipoint observation, co-observation, and distributed apertures. To accomplish these tasks, the system enables spacecrafts within a distributed spacecraft system to communicate science and coordination information, to determine relative position, velocity and time for command and control operations, and to operate in a coordinated manner to achieve common mission goals.

Claims

1. An integrated navigation and communication system contained within a spacecraft, that enables control operations and science operations in a distributed spacecraft system including multiple spacecrafts, comprising:

a stackable connector utilized as a system bus;

at least one processor card;

at least one GPS receiver card;

at least one crosslink receiver card for receiving signals from other spacecraft in the distributed spacecraft system; and

at least one crosslink transmitter card for transmitting signals to the other spacecraft in the distributed spacecraft system;

wherein the at least one processor card, the at least one GPS receiver card, the at least one crosslink receiver card, and the at least one crosslink transmitter card are in communication with each other by each being connected to the stackable connector.

2. The system as described in claim 1 wherein the at least one crosslink receiver card supports multiple frequency channels.

3. The system as described in claim 1 wherein the stackable connector provides access to a mezzanine memory board that supports multiple memory configurations that are adaptable for a given implementation.

4. The system as described in claim 1 wherein the at least one processor card supports signal acquisition and tracking, navigation, communications, and distributed command and control for the spacecraft.

5. The system as described in claim 1 further comprising at least one heat sink footing to dissipate thermal energy from the system to the spacecraft.

6. The system as described in claim 1 wherein the at least one processor card, the at least one GPS receiver card, the at least one crosslink receiver card, and the at least one crosslink transmitter card are positioned to mitigate EMI.

7. The system as described in claim 1 further comprising isolation plates fixed between the at least one processor card, the at least one GPS receiver card, the at least one crosslink receiver card, and the at least one crosslink transmitter card to mitigate EMI.

8. The system as described in claim 1 wherein the at least one processor card is programmable to a particular application using a field programmable array.

9. The system as described in claim 1 wherein the at least one GPS receiver card provides autonomous orbit determination and navigation based on an extended Kalman filter.

10. The system as described in claim 1 wherein the at least one crosslink receiver card supports at least one of a TDMA mode, a CDMA mode, or a hybrid FDMA/CDMA mode.

11. The system as described in claim 1 wherein the at least one crosslink transmitter card supports at least one of a TDMA mode, a CDMA mode, or a hybrid FDMA/CDMA mode.

12. The system as described in claim 1 wherein the at least one processor card supports adaptive power control to mitigate near-far communication interference.

13. The system as described in claim 1 wherein the at least one processor card supports centralized, hierarchical, and fully distributed command/control architectures.

14. The system as described in claim 1 wherein the at least one processor card supports relative navigation integrated crosslink communication and ranging capabilities.

15. The system as described in claim 1 wherein power, mass, and volume format design is a function of an intended mission.

16. The system as described in claim 1 wherein the stackable connector allows for an implementation of at least one additional card, thereby providing scalability to the system.

17. The system as described in claim 16, wherein an additional card is an uplink communication card, a downlink communication card, a High Data Rate (HDR) card, a power amplifier card, or a power conversion card.

18. The system as described in claim 1 wherein the at least one crosslink receiver card and the at least one crosslink transmitter card perform communication tasks and relative ranging tasks.

19. The system as described in claim 1 wherein the at least one processor card supports autonomous adaptive data rate control to mitigate near-far communication interference.