US3558058A — Thrust vectorable supersonic nozzle

Claim 1

Independent Claim 213 words

In a two-dimensional thrust vectorable supersonic nozzle; a centerbody structure initially positioned in centered relation within the exhaust nozzle portion and adapted to normally divide the nozzle exhaust gas flow into an upper and a lower path directing the exhausting gas products in a rearwardly direction representing the horizontally oriented flight mode of operation; an upper nozzle system adapted to form one nozzle wall portion and being separated from one side of said centerbody structure to thereby form an upper gas flow path in combination with said centerbody structure; a lower nozzle system adapted to form a second nozzle wall portion oppositEly disposed from said firstnamed nozzle wall portion and being similarly separated from the opposite side of said centerbody structure to thereby form therewith a lower gas flow path; first actuating means operably associated with said upper and lower nozzle systems and adapted to respectively reposition said nozzle systems relatively inwardly simultaneously in an inward and an outwardly position of adjustment respectively representing the transonic and supersonic horizontal flight modes of operation; and second actuating means operably interconnected with said centerbody structure and said upper and lower nozzle systems and adapted to collectively readjust said centerbody structure and nozzle systems to a downwardly directed configuration representing the vertical flight mode of operation.

Claim 2

Dependent Claim 213 words

In a two-dimensional thrust vectorable supersonic nozzle; a centerbody structure initially positioned in centered relation within the exhaust nozzle portion and adapted to normally divide the nozzle exhaust gas flow into an upper and a lower path directing the exhausting gas products in a rearwardly direction representing the horizontally oriented flight mode of operation; an upper nozzle system adapted to form one nozzle wall portion and being separated from one side of said centerbody structure to thereby form an upper gas flow path in combination with said centerbody structure; a lower nozzle system adapted to form a second nozzle wall portion oppositEly disposed from said firstnamed nozzle wall portion and being similarly separated from the opposite side of said centerbody structure to thereby form therewith a lower gas flow path; first actuating means operably associated with said upper and lower nozzle systems and adapted to respectively reposition said nozzle systems relatively inwardly simultaneously in an inward and an outwardly position of adjustment respectively representing the transonic and supersonic horizontal flight modes of operation; and second actuating means operably interconnected with said centerbody structure and said upper and lower nozzle systems and adapted to collectively readjust said centerbody structure and nozzle systems to a downwardly directed configuration representing the vertical flight mode of operation.

Claim 3

Dependent Claim 111 words

In a two-dimensional thrust vectorable supersonic nozzle as in claim 1, wherein said first-named actuating means incorporates a first and a second gas flow path-diverting mechanism respectively comprising said upper and lower nozzle systems and each being adjustable between a first, horizontally oriented position for respectively exhausting the separated gas flow rearwardly along the said upper and lower gas flow paths representing the horizontal mode of transonic and/or supersonic flight, and a second vertically oriented position of adjustment for directing the separate exhausting gas flows into a single, combined gas flow directed substantially along a single gas flow path disposed at an approximately 90* angle to the horizontal mode of operation.

Claim 4

Dependent Claim 98 words

In a two-dimensional thrust vectorable supersonic nozzle as in claim 1, wherein said second-named actuating means comprises a fixed centerbody structural element adapted to form part of the nozzle structure, and a centerbody flap mechanism movably mounted on, and adjustable relative to said fixed element for repositioning between its normally centered position forming the said two separate and horizontally directed gas flow paths to a second position of adjustment facilitating the conversion and direction of the said separate gas flows into the said single combined gas flow path diverted into the downwardly and vertically oriented flight mode configuration.

Claim 5

Dependent Claim 183 words

In a two-dimensional thrust vectorable supersonic nozzle as in claim 2, wherein said first-named gas flow path-diverting mechanism comprises an upper primary flap device positioned in, and forming part of the upper nozzle system at a relatively upstream location therein and operative on the main gas flow; and a second upper nozzle system flap device positioned immediately downstream of said primary flap device and formed in tandem relation therewith and thereby adapted to be cojointly operated during the transition phase of flight operation; and said second gas flow path-diverting mechanism comprising a similar lower primary flap device positioned in, and forming part of the lower nozzle system and located at an upstream position directly opposite of said upper primary flap device; and further having a second flap device positioned immediately downstream thereof and similarly corresponding to that of said upper nozzle system and likewise acting in tandem relation both with said lower primary flap device and with said upper nozzle system gas flow path-diverting mechanism for thereby collectively moving inwardly and outwardly during the transition phase between the transonic and supersonic flight modes.

Claim 6

Dependent Claim 80 words

In a two-dimensional thrust vectorable supersonic nozzle as in claim 4, and a pair of pressure-actuated and oppositely positioned outermost flaps located at the extreme exhaust downstream end portion opening of said nozzle for thereby providing added exit area capability to said nozzle, and simultaneously and automatically adapted to streamline with the gas flow being exhausted therethrough to thereby reduce the normal length and actuation loads required for repositioning the second-named flap devices for both upper and lower nozzle systems.

Claim 7

Dependent Claim 115 words

In a two-Dimensional thrust vectorable supersonic nozzle as in claim 1, wherein said centerbody structure further comprises a fixed body element forming part of the nozzle structure, and a pair of flap elements pivotally mounted at the same pivot to said fixed body element and respectively movable in joint action with each other and between a centered relation in the said nozzle to thereby assist in changing the previously separate upper and lower gas flows being exhausted rearwardly during the horizontal flight mode into a single combined gas flow directed substantially vertically downwardly for exhausting out of an opening provided by the further adjustment of said lower nozzle system in the nozzle surface associated therewith.

Claim 8

Dependent Claim 84 words

In a two-dimensional thrust vectorable supersonic nozzle as in claim 6, said pair of centerbody flap elements further comprising a first, downstream flap interconnected with a second, upstream flap and releasably affixed for simultaneous movement therewith and thereby readjust the combined positions thereof downwardly and upwardly in respective contact with the upper nozzle wall structure to thereby seal the said upper nozzle system flow path against further substantially horizontal gas flow therethrough and redirect the said flow downwardly in the vertical flight mode configuration.

Claim 9

Dependent Claim 154 words

In a two-dimensional thrust vectorable supersonic nozzle as in claim 7, wherein said fixed centerbody element incorporates a first cam element initially engaging with a cam follower fixed to said centerbody upstream flap; and said centerbody downstream flap further incorporating a second cam engaging with and moving said cam follower and the said upstream flap affixed thereto in contact with said first-named cam until reaching a latched position therewithin and in sealing contact with the upper nozzle system wall surface to thereby close off the upper gas flow path; said centerbody downstream flap thereafter disengaging from said upstream flap and continuing to rotate to a substantially vertical position closing off the lower nozzle assembly gas flow path in preparation for transitioning the nozzle operation from the horizontal to the vertical flight mode by defining one side of the combined flow path formed by the subsequent adjustment of said upper and lower nozzle system flaps.

Claim 10

Dependent Claim 83 words

In a two-dimensional thrust vectorable supersonic nozzle as in claim 8, and a third flap device pivoted at one end thereof to said centerbody fixed body element and interconnected at its other end by cam means with said second, upstream centerbody flap to thereby rotate upwardly with said second upstream flap, on movement of the latter by operation of said first-named centerbody flap, to thereby provide a relatively smooth transition surface at the entry of the throat portion of said upper nozzle system.

Claim 11

Dependent Claim 117 words

In a two-dimensional thrust vectorable supersonic nozzle as in claim 9, wherein the said downstream-positioned lower nozzle system flap is interconnected with a third actuating means adapted to readjust said flap and automatically repositioning said lower primary flap concurrently with the repositioning of said upper nozzle system tandem-mounted flaps and said centerbody system to thereby orient the said nozzle into its vertical flight mode configuration; said upper and lower nozzle assemblies each having a movably mounted and relatively elongated panel member pivotally mounted thereto for providing a continuous external flow surface during high Mach conditions and being further adapted to fold down in flush relation with the downstream upper and lower flaps corresponding thereto during transonic conditions.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1974-01-25	1974-07-27	1975-01-26	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	1978-01-25	1978-07-27	1979-01-26	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	1982-01-25	1982-07-27	1983-01-26	$7700.00	Window Closed / Lapsed

Thrust vectorable supersonic nozzle

Abstract

Inventors

Bibliographic Details

Claims Analysis

References Cited (Backward Citations)

USPTO Annuity & Maintenance Windows

Assigned Categories & Tags

Assign Category Tag