Self-adapting escape slide

• US 20030080254A1
• Filed: 10/26/2001
• Published: 05/01/2003
• Est. Priority Date: 10/26/2001
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Alberts, Jeff H.
• Granted Patent: US 6,676,082 B2
• Time in Patent Office: Days
• US Class Current: 244/137.2
• CPC Class Codes: A62B 1/20 by making use of sliding-ropes, sliding-poles or chutes, e.g. hoses, pipes, sliding-grooves, sliding-sheets
• CPC Class Codes: B64D 25/14 Inflatable escape chutes

Abstract

The present invention comprises a system for determining and adjusting the angle at which an escape slide is oriented. The system comprises an inflatable slide having a primary inflatable slide segment and at least one additional slide segments attached to the primary slide segment. Additionally, a state sensor configured to determine the attitude of the slide when inflated is attached to the slide or to structure surrounding the slide. Further, the system includes an inflation gas source coupled to the primary and at least one additional inflatable slide segments and an inflation controller in communication with the inflation gas source and the state sensor. The gas source and the state sensor operate to cause the gas source to adjust the at least one additional slide segments as a function of the attitude measured by the state sensor.

Claims

1. An inflatable slide, comprising:

a primary inflatable slide segment;

at least one additional slide segments attached to the primary slide segment;

a state sensor configured to determine the attitude of the slide;

an inflation gas source coupled to the primary and at least one additional inflatable slide segments; and

,

an inflation controller in communication with the inflation gas source and the state sensor to cause the gas source to inflate or deflate the at least one additional slide segments as a function of the attitude measured by the state sensor.

2. The slide of claim 1, wherein the state sensor is an electrolytic inclination sensor.

3. The slide of claim 1, wherein the state sensor is a semi-rigid sensor arm and contact sensor array.

4. The slide of claim 1, wherein the inflation gas source is a compressed gas.

5. The slide of claim 1, wherein the inflation gas source is an oxidation process.

6. The slide of claim 1, wherein the state sensor is attached to the slide.

7. The slide of claim 1, further comprising a deployment attitude sensor.

8. The slide of claim 1, wherein upon initial deployment, the primary slide segment and the additional slide segments are inflated, and if necessary, at least one of the additional slide segments are deflated to obtain optimal slide geometry.

9. The slide of claim 1, wherein upon initial deployment, only the primary slide segment is inflated, at least one of the additional slide segments being inflated as necessary to attain optimal slide geometry.

10. An aircraft escape slide, comprising:

a primary inflatable slide segment having a first end attached to an aircraft access point;

at least one additional slide segments attached to a second end of the primary slide segment;

a state sensor configured to determine the attitude of the aircraft at the aircraft access point;

an inflation gas source coupled to the primary and at least one additional inflatable slide segments; and

,

an inflation controller in communication with the inflation gas source and the state sensor to cause the gas source to pressurize the at least one additional slide segments as a function of the attitude measured by the state sensor.

11. The slide of claim 10, wherein the state sensor is a electrolytic inclination sensor.

12. The slide of claim 10, wherein the state sensor is a mercury contact sensor array.

13. The slide of claim 10, wherein the inflation gas source is a compressed gas.

14. The slide of claim 10, wherein the inflation gas source is an oxidation process.

15. The slide of claim 10, wherein the state sensor is attached to the aircraft.

16. The slide of claim 10, further comprising a predicting the slide attitude based upon the attitude of the aircraft access point.

17. The slide of claim 10, wherein upon initial deployment, the primary slide segment and the additional slide segments are inflated, and if necessary, at least one of the additional slide segments are deflated to obtain optimal slide geometry.

18. The slide of claim 10, wherein upon initial deployment, only the primary slide segment is inflated, at least one of the additional slide segments being inflated as necessary to attain optimal slide geometry.

19. A method of deploying an aircraft escape slide, comprising:

deploying a slide attached to an aircraft, the slide having a primary inflatable slide segment attached to an at least one additional slide segment;

activating a timing device or pressure sensor;

waiting a pre-determined time or until a pre-determined pressure is achieved;

determining a slide angle;

determining if the slide angle is within operating slide angle tolerances;

adjusting the slide angle, if necessary, via pressure control within the at least one additional slide segment in order to bring the slide angle within operating tolerances.

20. The method of claim 19, wherein the step of determining a slide angle further comprises predicting an inflated slide geometry.