SAFE TAKEOFF MONITORING SYSTEM

• US 20130211636A1
• Filed: 12/12/2012
• Published: 08/15/2013
• Est. Priority Date: 12/22/2011
• Status: Active Grant

• Current Assignee: Embraer S.A.
• Original Assignee: Embraer S.A.
• Inventors: MARTINS, Reinaldo, Seibert, Nelson
• Granted Patent: US 10,315,777 B2
• Time in Patent Office: Days
• US Class Current: 701/15
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: G05D 1/0083 to help an aircraft pilot in the rolling phase

Abstract

A safe takeoff monitoring system checks the actual physical parameters of an airplane during takeoff, determines the actual takeoff weight, and warns the pilot to interrupt the takeoff if any dangerous situation is developing, before a high energy abort is necessary.

Claims

1. A safe takeoff monitoring system for an airplane, the system comprising:

sensors onboard the airplane that detect parameters relating to airplane weight; and

an automatic processor operatively coupled to the sensors, the automatic processing system continually computing parameters including distance required for stopping the airplane from its present position, the automatic processor conditionally issuing a warning to the pilot to abort takeoff if the remaining distance on the runway is adequate to stop the airplane and the actual airplane speed is below V_R.

2. The system of claim 1 wherein said automatic processor computes airplane actual instantaneous weight in response to the sensors.

3. The system of claim 1 wherein the automatic processor computes minimum acceptable rotation speed.

4. The system of claim 1 wherein the automatic processor computes distances required to attain rotation, lift-off and 35 foot-height above the runway, considering an all-engine-operating condition.

5. The system of claim 1 wherein the automatic processor evaluates the energy absorbed by the airplane brakes in case of an aborted takeoff.

6. The system of claim 1 wherein the automatic processor evaluates the climb gradient available at lift-off, considering an all-engine-operating condition.

7. The system of claim 1 wherein the automatic processor warns the pilot to abort takeoff if a large deviation is detected between the airplane weight as determined by the automatic processor and one inputted by the pilot.

8. The system of claim 1 wherein the automatic processor warns the pilot to abort takeoff if rotation speed proposed by the pilot is lower than the minimum acceptable for actual airplane operating conditions.

9. The system of claim 1 wherein the automatic processor issues an abort warning only when the airplane energy is within the absorption capability of the airplane brakes.

10. A safe takeoff monitoring method for an airplane, the method comprising:

sensing using electronic sensors onboard the airplane;

using at least one processor, continually computing parameters in response to the sensing, including distance required for stopping the airplane from its present position, and

using the at least one processor, issuing a warning to the pilot to abort takeoff if the remaining distance on the runway is adequate to stop the airplane and the actual airplane speed is below V_R.

11. The method of claim 10 further including computing airplane actual instantaneous weight.

12. The method of claim 10 further including computing minimum acceptable rotation speed.

13. The method of claim 10 further including computing distances required to attain rotation, lift-off and 35 foot-height above the runway, considering an all-engine-operating condition.

14. The method of claim 10 further including evaluating the energy absorbed by the airplane brakes in case of an aborted takeoff.

15. The method of claim 10 further including evaluating the climb gradient available at lift-off, considering an all-engine-operating condition.

16. The method of claim 10 further including warning the pilot to abort takeoff if a large deviation is detected between the airplane weight as determined by the automatic processor and one inputted by the pilot.

17. The method of claim 10 further including warning the pilot to abort takeoff if rotation speed proposed by the pilot is lower than the minimum acceptable for actual airplane operating conditions.

18. The method of claim 10 further including issuing an abort warning only when the airplane energy is within the absorption capability of the airplane brakes.

19. A safe takeoff monitoring system for an airplane, the system comprising:

sensors onboard the airplane that detect parameters relating to airplane weight;

a pilot-interface system,

a take-off data consistency checker,

a calculation unit including a thrust calculator, equivalent air speed calculator and airplane weight calculator,

a VR calculation unit that calculates minimum VR, determines instantaneous distance to VR, calculates data from VR to V35, and applies safety criteria,

an available climb capability calculator,

a stopping distance calculator,

a brake energy calculator, and

a pilot warning system operatively coupled to the above-mentioned calculators that conditionally issues a warning to the pilot to abort takeoff if the remaining distance on the runway is adequate to stop the airplane and actual airplane speed is below VR.

20. A safe takeoff monitoring system for an airplane, the system comprising:

sensors onboard the airplane that detect parameters relating to airplane weight;

means for providing a pilot-interface,

means for checking take-off data consistency,

means for calculating thrust,

means for calculating equivalent air speed,

means for calculating airplane thrust to weight ratio,

VR calculation means for calculating minimum VR, determining instantaneous distance to VR, calculating data from VR to V35, and applying safety criteria,

means for calculating available climb capability,

means for calculating a stopping distance,

means for calculating brake energy, and

a pilot warning unit operatively coupled to the above-mentioned means that conditionally issues a warning to the pilot to abort takeoff if the remaining distance on the runway is adequate to stop the airplane and actual airplane speed is below VR.

21. The system of claim 20 wherein the pilot warning unit comprises means for conditionally issuing a warning to the pilot to abort takeoff if the remaining distance on the runway is adequate to stop the airplane and actual airplane speed is below VR.