Systems and methods for dynamic implementation of increased glide slope angles in approach procedures

1. A method for glide slope evaluation for an aircraft, the method comprising:

in a control module,

retrieving, from a navigation database (NDB), a designated approach procedure;

identifying a designated glide slope angle (D_GSA) from a final capture altitude (FCA) to an intersection point on a landing threshold of a runway, based on the designated approach procedure;

receiving sensor data from on-board sensors providing real-time environmental information near the aircraft;

receiving real-time navigation data providing a real-time aircraft location and heading of the aircraft;

receiving real-time avionics systems data including engine systems data, autopilot data, and auto-thrust data;

determining that an engine system, an autopilot system, and an auto-thrust system are operating optimally based on the avionics data;

generating an adaptive glide slope angle (A_GSA) from the FCA to the intersection point on the landing threshold of the runway, the A_GSA being larger than the D_GSA, the A_GSA being reflective of the real-time navigation data, real-time sensor data, and optimal operation of the engine system, the autopilot system, and the auto-thrust system;

determining whether (a) an altitude constraint applies at the FCA;

determining whether (b) a level segment exists at the FCA;

enabling modification of the designated approach procedure with the A_GSA, upon concurrence of (a) and (b); and

barring modification of the designated approach procedure with the A_GSA when there is no concurrence of (a) and (b).

2. The method of claim 1 , wherein the FCA is one from the set including: a glide slope intercept altitude (GSIA) and a final approach fix (FAF).

3. The method of claim 2 , further comprising generating an alert when there is no concurrence of (a) and (b).

4. The method of claim 2 , wherein generating the adaptive glide slope angle (A_GSA) and the associated final capture altitude (FCA) is further based on determining that there is favorable weather near the aircraft.

5. The method of claim 4 , wherein generating the adaptive glide slope angle (A_GSA) and the associated final capture altitude (FCA) is further based on determining that there is an object free zone near the aircraft.

6. The method of claim 5 , wherein generating the adaptive glide slope angle (A_GSA) and the associated final capture altitude (FCA) is further based on determining that aircraft braking mechanisms are working properly.

7. The method of claim 2 , wherein a ratio of the generated A_GSA to the D_GSA is less than 1.5.

8. The method of claim 6 , further comprising updating an image on a display system subsequent to enabling modification of the designated approach procedure.

9. A system for glide slope evaluation in an aircraft, the system comprising:

a navigation database providing a designated approach procedure;

a navigation system providing a real-time aircraft location and a heading of the aircraft;

an on-board sensor system providing real-time environmental status information near the aircraft;

avionics systems providing real-time avionics systems data including engine systems data, autopilot data, and auto-thrust data;

a control module operationally coupled to the navigation database, navigation system, avionics systems, and the on-board sensor system, the control module configured to,

identify a designated glide slope angle (D_GSA) from a final capture altitude (FCA) to an intersection point on a landing threshold of a runway, based on the designated approach procedure;

determine that an engine system, an autopilot system, and an auto-thrust system are operating optimally based on data received from the avionics systems;

generate an adaptive glide slope angle (A_GSA) from the FCA to the intersection point on the landing threshold of the runway, the A_GSA being larger than the D_GSA, the A_GSA being reflective of the real-time navigation data, data from the on-board sensor system, and optimal operation of the engine system, the autopilot system, and the auto-thrust system;

determine whether (a) an altitude constraint applies at the FCA;

determine whether (b) a level segment exists at the FCA;

enable modification of the designated approach procedure with the A_GSA, upon concurrence of (a) and (b); and

prevent modification of the designated approach procedure with the A_GSA when there is no concurrence of (a) and (b).

10. The system of claim 9 , wherein the FCA is one from the set including: a glide slope intercept altitude (GSIA) and a final approach fix (FAF).

11. The system of claim 10 , wherein the control module is further configured to generate an alert when there is no concurrence of (a) and (b).

12. The system of claim 10 , wherein the control module is further configured to generate the adaptive glide slope angle (A_GSA) and the associated final capture altitude (FCA) based on determining that there is favorable weather near the aircraft.

13. The system of claim 12 , wherein the control module is further configured to generate the adaptive glide slope angle (A_GSA) and the associated final capture altitude (FCA) based on determining that there is an object free zone near the aircraft.

14. The system of claim 13 , wherein the control module is further configured to generate the adaptive glide slope angle (A_GSA) and the associated final capture altitude (FCA) based on determining that aircraft braking mechanisms are working properly.

15. The system of claim 14 , wherein a ratio of the generated A_GSA to the D_GSA is less than 1.5.

16. The system of claim 15 , the control module is further configured to update an image on a display system, subsequent to enabling modification of the designated approach procedure.