Predictive aircraft flight envelope protection system

Abstract

The aircraft threat envelope protection system employs a threat envelope data structure in a computer-readable medium that stores at least one trigger condition for each of a plurality of different types of threats associated with the aircraft, and modeled using a common schema. A processor computes plural different projected trajectories representing different possible aircraft paths through spacetime. The processor associates at least some of the plurality of the threats to specific trigger points in spacetime along each of the projected trajectories. The processor will deprecate ones of the projected trajectories when they are deemed not viable to recover from a threat. The processor initiates an aircraft protective response when all projected trajectories but one have been deprecated and the aircraft is within a predetermined proximity to the closest trigger point in spacetime along the non-deprecated trajectory.

Description

[0001] Cross References to Related Applications [0002] Pursuant to 35 U.S.C. §229(e), this application claims priority to U.S. Provisional Application No. 62 / 723,227, filed August 27, 2018, entitled "AircraftFlight Envelope Protection Framework," the entire disclosure, drawings and appendices of which are adopted by References are included here. technical field [0003] The present disclosure relates generally to aircraft flight envelope protection systems, and more particularly to aircraft flight envelope protection systems that model potential aircraft trajectories and test those trajectories for aircraft restriction violations and terrain avoidance hazards. Background technique [0004] This section provides background information related to the present disclosure which is not necessarily prior art. [0005] Aircraft are designed to operate at certain operating speeds and loads on the control surfaces of the aircraft. These operating limits are known as the flight env...

AI Technical Summary

Problems solved by technology

These traditional systems do not account for high altitude terrain where climb performance is significantly lower than sea level, nor do they account for gross weight effects or engine failure conditions

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