Deployable inlet for aeroplane center boost engine

Claim 2

In combination with an aircraft having a fuselage; an empennage including an empennage body structure and an upstanding vertical stabilizer mounted on said fuselage and having a leading edge and spaced port and starboard skin panels defining smooth, aerodynamically streamlined skin surfaces extending rearwardly from said stabilizer leading edge; and of the type including an auxiliary center boost jet engine having a rearwardly directed exhaust nozzle mounted within said empennage body structure, an air inlet formed in and coincident with said leading edge of said stabilizer, and an air inlet duct extending from said air inlet to said center boost jet engine and being enclosed wholly within said vertical stabilizer and said empennage body structure; a deployable air inlet comprising: (a) port and starboard air inlet closure members respectively formed by lower leading edge quarter chord door panels defining portions of said port and starboard aerodynamically streamlined skin surfaces of said stabilizer; (b) said port and starboard air inlet closure members defining a forwardly presented generally vertical parting line coincident with said stabilizer leading edge with said members respectively lying in the planes of said stabilizer port and starboard skin surfaces when in the closed position so as to form smooth aerodynamically streamlined continuations of said port and starboard stabilizer skin surfaces extending rearwardly from said stabilizer leading edge; (c) said port and starboard closure members having their rearmost generally vertical quarter chord door panel edges pivotally secured to said stabilizer along lines generally parallel to said stabilizer leading edge and lying in the planes of said port and starboard skin surfaces when in the closed position; (d) means for rotating said port and starboard closure members about their pivotal connections to said stabilizer between: (i) a first position wherein the leading edges of said closure members are in abutting sealing relation along said parting line coincident with said stabilizer leading edge so as to close and seal said air inlet when said aircraft is being operated in a cruise operational mode and said center boost jet engine is shut down; and (ii), a second position wherein said port and starboard closure members are pivoted outwardly and in opposite directions from said parting line coincident with said stabilizer leading edge so as to define said air inlet's highlight and throat geometry during power assist operational modes of the aircraft when said center boost jet engine is operational; (e) said port and starboard closure members being spaced above the juncture between said vertical stabilizer and said fuselage; and, (f) means for precluding entry of fuselage boundary layer air into said air inlet when said port and starboard closure members are in said second position.

Claim 3

A deployable air inlet as set forth in claim 1 wherein said port and starboard closure members are substantially trapezoidal in configuration having essentially parallel upper and lower edges with their leading and trailing edges slanted rearwardly and defining acute included angles with the horizontal.

Claim 4

A deployable air inlet as set forth in claims 1 or 2 wherein said means for precluding entry of fuselage boundary layer air into said air inlet comprises lower horizontal fence means mounted on said stabilizer immediately below said closure members, upper fence means being mounted on said stabilizer immediately above said closure members, and wherein said closure members and said upper and lower fence means define said air inlet's highlight and throat geometry when said closure members are pivoted outwardly to their deployed second positions.

Claim 5

In an aircraft having an empennage including an empennage body structure and an upstanding vertical stabilizer having a leading edge and spaced port and starboard skin panels defining smooth, aerodynamically streamlined skin surfaces extending rearwardly from the stabilizer leading edge, and of the type including an auxiliary center boost jet engine having a rearwardly directed exhaust nozzle mounted within the empennage body structure and an air inlet duct extending from an air inlet formed in the root leading edge of the stabilizer to the center boost jet engine, a deployable air inlet comprising, in combination: (a) port and starboard air inlet closure members respectively formed by lower leading edge quarter chord door panels defining portions of the port and starboard aerodynamically streamlined skin surfaces of the stabilizer; (b) said port and starboard air inlet closure members defining a forwardly presented generally vertical parting line coincident with the stabilizer leading edge with said members respectively lying in the planes of the stabilizer port and starboard skin surfaces when in the closed position so as to form smooth aerodynamically streamlined continuations of the port and starboard stabilizer skin surfaces extending rearwardly from the stabilizer leading edge; (c) said port and starboard closure members having their rearmost generally vertical quarter chord door panel edges pivotally secured to the stabilizer along lines generally parallel to the stabilizer leading edge and lying in the planes of the port and starboard skin surfaces; (d) upper and lower horizontal fence means mounted on the stabilizer with said upper fence means being positioned immediately above said closure members and said lower fence means being positioned immediately below said closure members, said upper and lower fence means fairing outwardly in a horizontal plane from the stabilizer's skin surfaces and leading edge, whereby said closure members and said upper and lower fence means define said air inlet's highlight and throat geometry and said lower fence means preclude entry of fuselage boundary layer air into said air inlet when said closure members are pivoted outwardly to their deployed positions; and, (e) means for rotating said port and starboard closure members about their pivotal connections to the stabilizer between: (i) a first position wherein the leading edges of said closure members are in abutting sealing relation along said parting line coincident with the stabilizer leading edge so as to close and seal said air inlet when the aircraft is being operated in a cruise operational mode and the center boost jet engine is shut down; and (ii), a second position wherein said port and starboard closure members are pivoted outwardly and in opposite directions from said parting line so as to define said air inlet's highlight and throat geometry during power assist operational modes of the aircraft when the center boost jet engine is operational.

Claim 6

In an aircraft having an empennage including an empennage body structure and an upstanding vertical stabilizer having a leading edge and spaced port and starboard skin panels defining smooth, aerodynamically streamlined skin surfaces extending rearwardly from the stabilizer leading edge, and of the type including an auxiliary center boost jet engine having a rearwardly directed exhaust nozzle mounted within the empennage body structure and an air inlet duct extending from an air inlet formed in the root leading edge of the stabilizer to the center boost jet engine, a deployable air inlet comprising, in combination: (a) port and starboard air inlet closure members respectively formed by lower leading edge quarter chord door panels defining portions of the port and starboard aerodynamically streamlined skin surfaces of the stabilizer; (b) said port and starboard air inlet closure members defining a forwardly presented generally vertical parting line coincident with the stabilizer leading edge with said members respectively lying in the planes of the stabilizer port and starboard skin surfaces when in the closed position so as to form smooth aerodynamically streamlined continuations of the port and starboard stabilizer skin surfaces extending rearwardly from the stabilizer leading edge; (c) said port and starboard closure members having their rearmost generally vertical quarter chord door panel edges pivotally secured to the stabilizer along lines generally parallel to the stabilizer leading edge and lying in the planes of the port and starboard skin surfaces; (d) upper and lower horizontal fence means mounted on the stabilizer with said upper fence means being positioned immediately above said closure members and said lower fence means being positioned immediately below said closure members, said upper and lower fence means fairing outwardly in a horizontal plane from the stabilizer's skin surfaces and leading edge, whereby said closure members and said upper and lower fence means define said air inlet's highlight and throat geometry and said lower fence means preclude entry of fuselage boundary layer air into said air inlet when said closure members are pivoted outwardly to their deployed positions; and, (e) means for rotating said port and starboard closure members about their pivotal connections to the stabilizer between: (i) a first position wherein the leading edges of said closure members are in abutting sealing relation along said parting line coincident with the stabilizer leading edge so as to close and seal said air inlet when the aircraft is being operated in a cruise operational mode and the center boost jet engine is shut down; and (ii), a second position wherein said port and starboard closure members are pivoted outwardly and in opposite directions from said parting line so as to define said air inlet's highlight and throat geometry during power assist operational modes of the aircraft when the center boost jet engine is operational.

Claim 7

A deployable air inlet as set forth in claim 4 wherein said port and starboard closure members are substantially trapezoidal in configuration having essentially parallel upper and lower edges with their leading and trailing edges slanted rearwardly and defining acute included angles with the horizontal.

Claim 8

A deployable air inlet as set forth in claim 5 wherein said closure members have a vertical dimension less than the vertical distance between said upper and lower fence means, upper and lower trim blocks telescopically mounted on said closure members with freedom for relative vertical movement with respect thereto, first biasing means for normally urging said upper trim blocks into engagement with said upper fence means, and second biasing means for normally urging said lower trim blocks into engagement with said lower fence means, whereby said trim blocks serve to fill any gaps between the upper and lower edges of said trapezoidal closure members and said upper and lower fence means at all operative positions of said closure members.

Claim 9

A deployable air inlet as set forth in claims 4 or 5 wherein said means for rotating said closure members includes synchronously and oppositely driven reversible rotary actuators passing through said pivotal connections between the stabilizer and said closure members for selectively and synchronously pivoting said closure members between closed and opened positions.

Claim 10

A deployable air inlet as set forth in claims 4 or 5 wherein said means for rotating said closure members includes synchronously and oppositely driven reversible rotary actuators for selectively and synchronously pivoting said closure members between closed and opened positions, and means for terminating pivotal movement of said closure members at any selected position ranging from fully closed through fully opened so as to permit control of said air inlet's throat area to meet operating requirements.

Claim 11

An aircraft of the type having multiple main propulsion engines, an empennage including an upstanding vertical stabilizer, and an auxiliary center boost jet engine mounted within said empennage and having a rearwardly extending exhaust nozzle and a forwardly extending air inlet duct communicating with an air inlet formed in the root leading edge of said empennage stabilizer, and comprising, in combination: (a) an empennage including an upstanding vertical stabilizer having a generally vertically oriented leading edge and port and starboard stabilizer surface panels defining smooth aerodynamically streamlined stabilizer skin surfaces extending rearwardly from said stabilizer leading edge; (b) port and starboard air inlet closure members respectively formed by lower leading edge quarter chord door panels defining portions of said port and starboard aerodynamically streamlined skin surfaces of said stabilizer; (c) said port and starboard air inlet closure members defining a forwardly presented generally vertical parting line coincident with said stabilizer leading edge with said members respectively lying in the planes of said stabilizer port and starboard skin surfaces when in the closed position so as to form smooth aerodynamically streamIined continuations of said stabilizer skin surfaces extending rearwardly from said stabilizer leading edge; (d) said port and starboard closure members having their rearmost generally vertical quarter chord door panel edges pivotally secured to said stabilizer along lines generally parallel to said stabilizer leading edge and lying in the planes of said port and starboard skin surfaces; (e) upper and lower horizontal fence means mounted on said stabilizer with said upper fence means being positioned immediately above said closure members and said lower fence means being positioned immediately below said closure members, said upper and lower fence means fairing outwardly in a horizontal plane from said stabilizer's skin surfaces and leading edge, whereby said closure members and said upper and lower fence means define said air inlet's highlight and throat geometry and said lower fence means preclude entry of fuselage boundary layer air into said air inlet when said closure members are pivoted outwardly to their deployed positions; and, (f) means for rotating said port and starboard closure members about their pivotal connections to said stabilizer between: (i) a first position wherein the leading edges of said closure members are in abutting sealing relation along said parting line coincident with said stabilizer leading edge so as to close and seal said air inlet when said aircraft is in a cruise operational mode and said center boost jet engine is shut down; and (ii), a second position wherein said port and starboard closure members are pivoted outwardly and in opposite directions from said parting line so as to define said air inlet's highlight and throat geometry during power assist operational modes of said aircraft when said center boost jet engine is operational.

Claim 12

An aircraft of the type having multiple main propulsion engines, an empennage including an upstanding vertical stabilizer, and an auxiliary center boost jet engine mounted within said empennage and having a rearwardly extending exhaust nozzle and a forwardly extending air inlet duct communicating with an air inlet formed in the root leading edge of said empennage stabilizer, and comprising, in combination: (a) an empennage including an upstanding vertical stabilizer having a generally vertically oriented leading edge and port and starboard stabilizer surface panels defining smooth aerodynamically streamlined stabilizer skin surfaces extending rearwardly from said stabilizer leading edge; (b) port and starboard air inlet closure members respectively formed by lower leading edge quarter chord door panels defining portions of said port and starboard aerodynamically streamlined skin surfaces of said stabilizer; (c) said port and starboard air inlet closure members defining a forwardly presented generally vertical parting line coincident with said stabilizer leading edge with said members respectively lying in the planes of said stabilizer port and starboard skin surfaces when in the closed position so as to form smooth aerodynamically streamIined continuations of said stabilizer skin surfaces extending rearwardly from said stabilizer leading edge; (d) said port and starboard closure members having their rearmost generally vertical quarter chord door panel edges pivotally secured to said stabilizer along lines generally parallel to said stabilizer leading edge and lying in the planes of said port and starboard skin surfaces; (e) upper and lower horizontal fence means mounted on said stabilizer with said upper fence means being positioned immediately above said closure members and said lower fence means being positioned immediately below said closure members, said upper and lower fence means fairing outwardly in a horizontal plane from said stabilizer's skin surfaces and leading edge, whereby said closure members and said upper and lower fence means define said air inlet's highlight and throat geometry and said lower fence means preclude entry of fuselage boundary layer air into said air inlet when said closure members are pivoted outwardly to their deployed positions; and, (f) means for rotating said port and starboard closure members about their pivotal connections to said stabilizer between: (i) a first position wherein the leading edges of said closure members are in abutting sealing relation along said parting line coincident with said stabilizer leading edge so as to close and seal said air inlet when said aircraft is in a cruise operational mode and said center boost jet engine is shut down; and (ii), a second position wherein said port and starboard closure members are pivoted outwardly and in opposite directions from said parting line so as to define said air inlet's highlight and throat geometry during power assist operational modes of said aircraft when said center boost jet engine is operational.

Claim 13

An aircraft as set forth in claim 9 wherein said port and starboard closure members are substantially trapezoidal in configuration having essentially parallel upper and lower edges with their leading and trailing edges slanted rearwardly and defining acute included angles with the horizontal.

Claim 14

An aircraft as set forth in claims 10 wherein said closure members have a vertical dimension less than the vertical distance between said upper and lower fence means, upper and lower trim blocks telescopically mounted on said closure members with freedom for relative vertical movement with respect thereto, first biasing means for normally urging said upper trim blocks into engagement with said upper fence means, and second biasing means for normally urging said lower trim blocks into engagement with said lower fence means, whereby said trim blocks serve to fill any gaps between the upper and lower edges of said trapezoidal closure members and said upper and lower fence means at all operative positions of said closure members.

Claim 15

An aircraft as set forth in claims 9, 10 or 11 wherein said means for rotating said closure members includes synchronously and oppositely driven reversible rotary actuators passing through said pivotal connections between said stabilizer and said closure members for selectively and synchronously pivoting said closure members between closed and opened positions.

Claim 16

An aircraft as set forth in claims 9, 10 or 11 wherein said means for rotating said closure members includes synchronously and oppositely driven reversible rotary actuators for selectively and synchronously pivoting said closure members between closed and opened positions, and means for terminating pivotal movement of said closure members at any selected position ranging from fully closed through fully opened so as to permit control of said air inlet's throat area to meet operating requirements.

Claim 17

An aircraft as set forth in claims 9, 10 or 11 wherein means are provided for optimizing the drag characteristics of said rearwardly extending exhaust nozzle when said aircraft is in a cruise operational mode and said center boost engine is shut down.