Detecting a low performance takeoff condition for aircraft for use with ground proximity warning systems

• US 20020021230A1
• Filed: 07/23/2001
• Published: 02/21/2002
• Est. Priority Date: 07/24/2000
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Johnson, Steven C.
• Granted Patent: US 6,437,707 B1
• Time in Patent Office: Days
• US Class Current: 340/945
• CPC Class Codes: G01C 23/005 Flight directors indicating arrangements specially adapted for rotary gyroscopes G01C19/32
• CPC Class Codes: G05D 1/0661 specially adapted for take-off
• CPC Class Codes: G08G 5/0021 located in the aircraft
• CPC Class Codes: G08G 5/0065 for taking-off
• CPC Class Codes: G08G 5/0086 for monitoring terrain radar or analogous systems specially adapted for terrain avoidance G01S13/935
• CPC Class Codes: G08G 5/045 Navigation or guidance aids, e.g. determination of anti-collision manoeuvers radar or analogous systems specially adapted for anti-collision between aircraft G01S13/933

Abstract

The present invention includes a system, method and computer program product for reducing nuisance warnings during low performance takeoff conditions. The system includes a first component that determines aircraft current climb rate and potential climb rate based on aircraft vertical speed data and velocity information and a second component that adds the determined current climb rate and potential climb rate. The system also includes a third component that disables alerts, if the sum of the current climb rate and potential climb rate differ from a predetermined climb rate by a threshold amount and if the aircraft is supposed to be in a maximum thrust condition (e.g. takeoff, missed approach).

Claims

1. A ground proximity warning method comprising:

determining aircraft current climb rate and potential climb rate based on aircraft vertical speed data and velocity information;

adding the determined current climb rate and potential climb rate; and

disabling alerts, if the sum of the current climb rate and potential climb rate differ from a predetermined climb rate by a threshold amount.

2. The method of claim 1, wherein the predetermined climb rate is based on all engine maximum thrust operation.

3. The method of claim 2, wherein the all engine maximum thrust operation is based on a drag component, a weight component, and an all engines at maximum thrust component.

4. A ground proximity warning system comprising:

a means for determining aircraft current climb rate and potential climb rate based on aircraft vertical speed data and velocity information;

a means for adding the determined current climb rate and potential climb rate;

and

a means for disabling alerts, if the sum of the current climb rate and potential climb rate differ from a predetermined climb rate by a threshold amount.

5. The system of claim 4, wherein the predetermined climb rate is based on all engine maximum thrust operation.

6. The system of claim 5, wherein the all engine maximum thrust operation is based on a drag component, a weight component, and an all engines at maximum thrust component.

7. A ground proximity warning system computer program product comprising:

a component configured to determine aircraft current climb rate and potential climb rate based on aircraft vertical speed data and velocity information;

a component configured to add the determined current climb rate and potential climb rate; and

a component configured to disable alerts, if the sum of the current climb rate and potential climb rate differ from a predetermined climb rate by a threshold amount.

8. The product of claim 7, wherein the predetermined climb rate is based on all engine maximum thrust operation.

9. The product of claim 8, wherein the all engine maximum thrust operation is based on a drag component, a weight component, and an all engines at maximum thrust component.

10. A ground proximity warning system comprising:

a component configured to determine aircraft current climb rate and potential climb rate based on aircraft vertical speed data and velocity information;

a component configured to add the determined current climb rate and potential climb rate; and

a component configured to disable alerts, if the sum of the current climb rate and potential climb rate differ from a predetermined climb rate by a threshold amount.

11. The system of claim 10, wherein the predetermined climb rate is based on all engine maximum thrust operation.

12. The system of claim 11, wherein the all engine maximum thrust operation is based on a drag component, a weight component, and an all engines at maximum thrust component.