VEHICLE COMMUNICATION SYSTEM AND METHOD

• US 20190007144A1
• Filed: 06/29/2017
• Published: 01/03/2019
• Est. Priority Date: 06/29/2017
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: TILLOTSON, Brian J.
• Granted Patent: US 10,693,567 B2
• Time in Patent Office: Days
• CPC Class Codes: B64G 1/22 Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
• CPC Class Codes: B64G 1/222 for deploying structures between a stowed and deployed state
• CPC Class Codes: B64G 1/42 Arrangements or adaptations of power supply systems
• CPC Class Codes: B64G 1/428 Power distribution and management
• CPC Class Codes: G08C 23/02 using infrasonic, sonic or ultrasonic waves
• CPC Class Codes: H04B 11/00 Transmission systems employing sonic, ultrasonic or infrasonic waves

Abstract

A spacecraft including a frame including a joint coupling a first frame portion to a second frame portion, and an acoustic communication system configured to transfer acoustic data signals across the joint between the first frame portion and the second frame portion.

Claims

1. A spacecraft comprising:

a frame including a joint coupling a first frame portion to a second frame portion; and

an acoustic communication system configured to transfer acoustic data signals across the joint between the first frame portion and the second frame portion.

2. The spacecraft of claim 1, wherein the joint includes a forced coupling system configured to bias the first frame portion against the second frame portion in a zero gravity environment so as to form an acoustic data transmission conduit from the first frame portion to the second frame portion.

3. The spacecraft of claim 2, wherein the forced coupling system comprises:

a lever arm coupled to one of the first frame portion and the second frame portion; and

a biasing member coupled to both the first frame portion and the second frame portion.

4. The spacecraft of claim 1, wherein the joint comprises:

a hinge pin;

a first hinge leaf including a first knuckle portion, the first Buckle portion pivotally coupling the first hinge leaf to the hinge pin; and

a second hinge leaf including a second knuckle portion, the second knuckle portion pivotally coupling the second hinge leaf to the hinge pin.

5. The spacecraft of claim 1, wherein the joint comprises:

a first joint portion having a longitudinal axis;

a second joint portion configured to move axially along the longitudinal axis of the first joint portion so as to form a telescoping joint; and

a biasing member disposed between the first joint portion and the second joint portion.

6. The spacecraft of claim 1, wherein the acoustic communication system comprises:

a first data module;

a first acoustic transducer in communication with the first data module, the first acoustic transducer being coupled to the first frame portion;

a second data module; and

a second acoustic transducer in communication with the second data module, the second acoustic transducer being coupled to the second frame portion.

7. The spacecraft of claim 6, wherein the acoustic communication system further comprises a media access control module coupled to at least the first acoustic transducer and the second acoustic transducer.

8. The spacecraft of claim 7, wherein the media access control module is configured to multiplex acoustic signals between at least the first acoustic transducer and the second acoustic transducer.

9. The spacecraft of claim 7, wherein the media access control module is configured to separate different acoustic data signals by polarizing the different acoustic data signals.

10. The spacecraft of claim 7, wherein the media access control module is configured to separate different acoustic data signals by assigning the different acoustic data signals to a respective predetermined acoustic signal type.

11. A spacecraft comprising:

a first frame portion;

a second frame portion;

a joint coupling the first frame portion to the second frame portion so as to form an acoustic data transmission conduit between the first frame portion and the second frame portion, the joint being configured to form the acoustic data transmission conduit in a zero gravity environment; and

an acoustic communication system configured to transfer acoustic data signals across the joint between the first frame portion and the second frame portion.

12. The spacecraft of claim 11, wherein the joint includes a forced coupling system configured to bias the first frame portion against the second frame portion in the zero gravity environment so as to form the acoustic data transmission conduit from the first frame portion to the second frame portion.

13. The spacecraft of claim 12, wherein the forced coupling system comprises:

a lever arm coupled to one of the first frame portion and the second frame portion; and

a biasing member coupled to both the first frame portion and the second frame portion.

14. The spacecraft of claim 11, wherein the joint comprises:

a hinge pin;

a first hinge leaf including a first knuckle portion, the first knuckle portion pivotally coupling the first hinge leaf to the hinge pin; and

a second hinge leaf including a second knuckle portion, the second knuckle portion pivotally coupling the second hinge leaf to the hinge pin.

15. The spacecraft of claim 11, wherein the joint comprises:

a first joint portion having a longitudinal axis;

a second joint portion configured to move axially along the longitudinal axis of the first joint portion so as to form a telescoping joint; and

a biasing member disposed between the first joint portion and the second joint portion.

16. A method for acoustic data transmission in a zero gravity environment, the method comprising:

forming an acoustic data transmission conduit with a joint, a first frame portion and a second frame portion where the joint movably couples the first frame portion and the second frame portion so that the first frame portion and the second frame portion are biased, in the zero gravity environment, in acoustic coupling contact; and

transmitting acoustic data signals from the first frame portion to the second frame portion through the joint.

17. The method of claim 16, wherein transmitting the acoustic data signals comprises transmitting the acoustic data signals between a first acoustic transducer coupled to the first frame portion and a second acoustic transducer coupled to the second frame portion.

18. The method of claim 16, further comprising multiplexing the acoustic data signals with a media access control module.

19. The method of claim 18, further comprising separating different acoustic data signals, with the media access control module, by polarizing the different acoustic data signals.

20. The method of claim 18, further comprising separating different acoustic data signals, with the media access control module, by assigning the different acoustic data signals to a respective predetermined acoustic signal type.