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Predictive aircraft flight envelope protection system

A protection system, aircraft technology, applied in traffic control systems, control/regulation systems, instruments, etc., to solve problems such as inability to land, aircraft losing flight envelope protection, regardless of gross weight effects or engine failure conditions

Pending Publication Date: 2021-04-16
GULFSTREAM AEROSPACE CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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
[0011] Also, these traditional systems are often not usable for landing based on whether the landing gear is down or commanded by the pilot
however, disabling the system will cause the vehicle to lose flight envelope protection during landing

Method used

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  • Predictive aircraft flight envelope protection system
  • Predictive aircraft flight envelope protection system
  • Predictive aircraft flight envelope protection system

Examples

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Embodiment Construction

[0030] The following detailed description is merely exemplary in nature and is not intended to limit the invention or the application and uses of the invention. Furthermore, there is no intention to be bound by any theory presented in the preceding background section or the following detailed description.

[0031] introduction

[0032] The disclosed aircraft flight envelope protection system uses flight path prediction techniques to provide a unified full envelope protection that operates over a full range of aircraft flight conditions for a full range of different types of hazards. A flight path prediction is continuously calculated from the current condition of the aircraft using a kinetic energy model. A plurality of predicted trajectories are computed, each representing a different escape route that enables recovery from the hazard when the hazard's threshold or trigger point is reached. The system considers different types of hazards, some involving inherent properties ...

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PUM

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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...

Claims

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Application Information

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IPC IPC(8): G08G5/00G05D1/10G08G5/04
CPCG05D1/106G08G5/0021G08G5/0086G08G5/045G08G5/0078G05D1/606
Inventor 凯文·普洛瑟T·兰德斯A·维迪亚A·萨哈伊B·芬莱森
Owner GULFSTREAM AEROSPACE CORP
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