Deflectable jet engine inlet

Claim 1

A system for ensuring continued power to the control surfaces of an aircraft during vertical descent of a horizontally oriented jet aircraft with a stalled engine, the system comprising: a deflector having an internal transversely arcuate surface with respect to an axis of the jet engine inlet and normally positioned substantially coaxial with the jet engine inlet for allowing unobstructed airflow through the inlet when the aircraft has substantial horizontal velocity; and means for pivotally displacing the arcuate deflector relative to the inlet when the aircraft undergoes vertical descent in a horizontal, stalled condition, thereby causing an interior surface of the deflector to reflect impinging vertical airflow only in a perpendicular direction, coaxial with the inlet for forcing sufficient airflow across the turbine blades of the engine to keep them rotating; hydraulic means connected to a shaft of the turbine blades; electric generating means connected to the shaft; and control means connected to the generating means and the hydraulic means for driving control surfaces of the aircraft sufficient to allow horizontal maneuvering of the stalled aircraft as the turbine blades and connected shaft are kept rotating by the reflected airflow.

Claim 2

A system for ensuring continued power to the control surfaces of an aircraft during vertical descent of a horizontally oriented jet aircraft with a stalled engine, the system comprising: a deflector having an internal transversely arcuate surface with respect to an axis of the jet engine inlet and normally positioned substantially coaxial with the jet engine inlet for allowing unobstructed airflow through the inlet when the aircraft has substantial horizontal velocity; and means for pivotally displacing the arcuate deflector relative to the inlet when the aircraft undergoes vertical descent in a horizontal, stalled condition, thereby causing an interior surface of the deflector to reflect impinging vertical airflow only in a perpendicular direction, coaxial with the inlet for forcing sufficient airflow across the turbine blades of the engine to keep them rotating; hydraulic means connected to a shaft of the turbine blades; electric generating means connected to the shaft; and control means connected to the generating means and the hydraulic means for driving control surfaces of the aircraft sufficient to allow horizontal maneuvering of the stalled aircraft as the turbine blades and connected shaft are kept rotating by the reflected airflow.

Claim 3

A method for selectively deflecting airflow through a jet engine inlet comprising the steps: maintaining an air deflector, having an internal transversely arcuate surface with respect to an inlet axis, in a non-obstructive position relative to the inlet during normal operation of an aircraft; and displacing the arcuate deflector outwardly from the inlet in response to a stalled engine condition thereby redirecting vertical airflow in a direction substantially only perpendicular, coaxial with the inlet when the aircraft undergoes vertical descent while being in an engine stalled horizontal condition.

Claim 4

A method for selectively deflecting airflow through a jet engine inlet comprising the steps: maintaining an air deflector, having an internal transversely arcuate surface with respect to an inlet axis, in a non-obstructive position relative to the inlet during normal operation of an aircraft; and displacing the arcuate deflector outwardly from the inlet in response to a stalled engine condition thereby redirecting vertical airflow in a direction substantially only perpendicular, coaxial with the inlet when the aircraft undergoes vertical descent while being in an engine stalled horizontal condition.