Office Action 1: Non-Final Rejection (2025-05-06)
Rejection types: 102 - Lack of Novelty, 103 - Obviousness, 112 - Written Description/Enablement

CLAIMS:
CLAIMS
1\. A thrust reverser, comprising: an outer articulating panel comprising an outer thrust reverser door pivotally coupled to the outer articulating panel, the outer thrust reverser door is movable between an outer door stowed position and an outer door deployed position with respect to the outer articulating panel; and an inner articulating panel comprising an inner thrust reverser door pivotally coupled to the inner articulating panel, the inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel; wherein the inner thrust reverser door and the outer thrust reverser door are configured to redirect exhaust gasses to generate reverse thrust to an aircraft.
2\. The thrust reverser of claim 1, wherein the inner articulating panel further comprises a forward inner skin and an aft inner skin.
3\. The thrust reverser of claim 2, wherein a nozzle throat is at least partially defined at an interface between the forward inner skin and the aft inner skin.
4\. The thrust reverser of claim 3, wherein the forward inner skin is configured to pivot to vary a nozzle throat area.
5.The thrust reverser of claim 3, further comprising a sliding joint offset from the interface between the forward inner skin and the aft inner skin, wherein the forward inner skin and the aft inner skin are coupled together at the sliding joint.
6\. The thrust reverser of claim 1, wherein a nozzle exit is at least partially defined at an aft end of the inner articulating panel.
7\. The thrust reverser of claim 6, wherein the outer articulating panel is configured to pivot to vary a nozzle exit area.
8\. The thrust reverser of claim 1, further comprising a first thrust reverser actuator configured to pivot the outer thrust reverser door with respect to the outer articulating panel between the outer door deployed position and the outer door stowed position.
9\. The thrust reverser of claim 8, further comprising a second thrust reverser actuator configured to pivot the inner thrust reverser door with respect to the inner articulating panel between the deployed inner door position and the stowed inner door position.
10\. The thrust reverser of claim 1, further comprising a first nozzle actuator configured to pivot the outer articulating panel.
11\. The thrust reverser of claim 10, further comprising a second nozzle actuator configured to pivot the forward inner skin.
12\. The thrust reverser of claim 11, further comprising: a first linear joint disposed between the first nozzle actuator and the outer articulating panel; and a second linear joint disposed between the second nozzle actuator and the forward inner skin.
13\. The thrust reverser of claim 12, further comprising: a third linear joint disposed between the first thrust reverser actuator and the outer thrust reverser door; and a fourth linear joint disposed between the second thrust reverser actuator and the inner thrust reverser door.
14\. The thrust reverser of claim 1, wherein the outer articulating panel further comprises an outer skin.
15\. The thrust reverser of claim 14, further comprising a flap located at a forward edge of the outer skin, wherein the flap is slidingly coupled to the outer skin to maintain a continuous aerodynamic surface while the outer articulating panel pivots.

OFFICE ACTION:
Notice of Pre-AIA  or AIA  Status
The present application, filed on or after March 16, 2013, is being examined under the first inventor to file provisions of the AIA .
DETAILED ACTION
Claim Rejections - 35 USC § 112
The following is a quotation of 35 U.S.C. 112(b):
(b)  CONCLUSION.—The specification shall conclude with one or more claims particularly pointing out and distinctly claiming the subject matter which the inventor or a joint inventor regards as the invention.
The following is a quotation of 35 U.S.C. 112 (pre-AIA ), second paragraph:
The specification shall conclude with one or more claims particularly pointing out and distinctly claiming the subject matter which the applicant regards as his invention.
Claims 11-13 are rejected under 35 U.S.C. 112(b) or 35 U.S.C. 112 (pre-AIA ), second paragraph, as being indefinite for failing to particularly point out and distinctly claim the subject matter which the inventor or a joint inventor (or for applications subject to pre-AIA  35 U.S.C. 112, the applicant), regards as the invention.
In claim 11, “the forward inner skin” lacks antecedent basis.
In claim 13, “the first thrust reverser actuator” and “the second thrust reverser actuator” lack antecedent basis.
Claim Rejections - 35 USC § 102
The following is a quotation of the appropriate paragraphs of 35 U.S.C. 102 that form the basis for the rejections under this section made in this Office action:
A person shall be entitled to a patent unless –
(a)(1) the claimed invention was patented, described in a printed publication, or in public use, on sale, or otherwise available to the public before the effective filing date of the claimed invention.
Claim(s) 1, 6-7, 14 is/are rejected under 35 U.S.C. 102(a)(1) as being anticipated by US 4836451 (Herrick).
Regarding claim 1, 6-7, 14 Herrick teaches a thrust reverser (Fig 4), comprising: an outer articulating panel comprising an outer thrust reverser door pivotally coupled to the outer articulating panel (outer thrust reverser door 64’ or 66’ pivotally coupled to outer articulating panel 56’ or 58’, respectively), the outer thrust reverser door is movable between an outer door stowed position and an outer door deployed position with respect to the outer articulating panel (64’ in a deployed position in Fig 4, a stowed position in Fig 5); and an inner articulating panel comprising an inner thrust reverser door pivotally coupled to the inner articulating panel (inner thrust reverser door 34’ or 36’ pivotally coupled to inner articulating panel annotated below), the inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel (inner door deployed position in Fig 4; stowed position construed as the open position wherein the exhaust nozzle is open – col 2 l. 61-col 3 l. 32); wherein the inner thrust reverser door and the outer thrust reverser door are configured to redirect exhaust gasses to generate reverse thrust to an aircraft (col 4 l. 61-col 5 l. 45), a nozzle exit is at least partially defined at an aft end of the inner articulating panel (Fig 4, 5), wherein the outer articulating panel is configured to pivot to vary a nozzle exit area (Fig 4-5, col 3 ll. 37-40; nozzle exit area at the aft end of the outer thrust reverser doors), the outer articulating panel further comprises an outer skin (one of the surfaces of 56’ or 58’ construed as a “skin”).
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Claim Rejections - 35 USC § 103
The following is a quotation of 35 U.S.C. 103 which forms the basis for all obviousness rejections set forth in this Office action:
A patent for a claimed invention may not be obtained, notwithstanding that the claimed invention is not identically disclosed as set forth in section 102, if the differences between the claimed invention and the prior art are such that the claimed invention as a whole would have been obvious before the effective filing date of the claimed invention to a person having ordinary skill in the art to which the claimed invention pertains. Patentability shall not be negated by the manner in which the invention was made.
Claim(s) 2-4 is/are rejected under 35 U.S.C. 103 as being unpatentable over US 4836451 (Herrick) in view of US 5779150 (Lidstone).
Regarding claim 2-4, Herrick fails to teach the inner articulating panel further comprises a forward inner skin and an aft inner skin, a nozzle throat is at least partially defined at an interface between the forward inner skin and the aft inner skin, wherein the forward inner skin is configured to pivot to vary a nozzle throat area. However, Lidstone teaches an inner articulating panel comprising a forward inner skin and an aft inner skin (Fig 8; forward inner skin 92, aft inner skin 94), a nozzle throat is at least partially defined at an interface between the forward inner skin and the aft inner skin, wherein the forward inner skin is configured to pivot to vary a nozzle throat area (Fig 6; interface between 92 and 94 forms the throat in one position; forward inner skin pivots relative to 90 and 94). It would have been obvious to one of ordinary skill in the art at the time of the invention to make the inner articulating panel further comprises a forward inner skin and an aft inner skin, a nozzle throat is at least partially defined at an interface between the forward inner skin and the aft inner skin, wherein the forward inner skin is configured to pivot to vary a nozzle throat area in order to allow for more complex shapes of the nozzle, as taught by Lidstone (col 5 l. 61-col 6 l. 9). It has been held that combining or simple substitution of prior art elements according to known methods to yield predictable results renders the limitation obvious (see MPEP 2141 (III)). In this case, making the inner articulating panel further comprises a forward inner skin and an aft inner skin, a nozzle throat is at least partially defined at an interface between the forward inner skin and the aft inner skin, wherein the forward inner skin is configured to pivot to vary a nozzle throat area yields predictable results.
Claim(s) 5 is/are rejected under 35 U.S.C. 103 as being unpatentable over US 4836451 (Herrick) in view of US 5779150 (Lidstone), and further in view of US 5103639 (Wolf).
Regarding claim 5, Herrick in view of Lidstone fails to teach a sliding joint offset from the interface between the forward inner skin and the aft inner skin, wherein the forward inner skin and the aft inner skin are coupled together at the sliding joint. However, Wolf teaches a sliding joint offset from the interface between the forward inner skin and the aft inner skin, wherein the forward inner skin and the aft inner skin are coupled together at the sliding joint (Fig 13-14, col 12 ll. 11-67; sliding joint including 76, 150, 152, 154 which joins the forward inner skin 62 and aft inner skin 64; sliding joint is offset from an interface between the forward and aft inner skins – pivoting interface at the forward end of 64). It would have been obvious to one of ordinary skill in the art at the time of the invention to provide a sliding joint offset from the interface between the forward inner skin and the aft inner skin, wherein the forward inner skin and the aft inner skin are coupled together at the sliding joint, as taught by Wolf. It has been held that combining or simple substitution of prior art elements according to known methods to yield predictable results renders the limitation obvious (see MPEP 2141 (III)). In this case, providing a sliding joint offset from the interface between the forward inner skin and the aft inner skin, wherein the forward inner skin and the aft inner skin are coupled together at the sliding joint yields predictable results.
Claim(s) 8-9 is/are rejected under 35 U.S.C. 103 as being unpatentable over US 4836451 (Herrick) in view of US 4690329 (Madden).
Regarding claim 8-9, Herrick fails to teach a first thrust reverser actuator configured to pivot the outer thrust reverser door with respect to the outer articulating panel between the outer door deployed position and the outer door stowed position and a second thrust reverser actuator configured to pivot the inner thrust reverser door with respect to the inner articulating panel between the deployed inner door position and the stowed inner door position. However, Madden teaches a first thrust reverser actuator configured to pivot the outer thrust reverser door and a second thrust reverser actuator configured to pivot the inner thrust reverser door (Fig 2, col 3 ll. 30-64, first actuator 67, second actuator 92). Furthermore, Herrick teaches that the inner thrust reverser door and the outer thrust reverser door may move independently of one another (see Fig 4-5; achieving different operating conditions). It would have been obvious to one of ordinary skill in the art at the time of the invention to provide a first thrust reverser actuator configured to pivot the outer thrust reverser door with respect to the outer articulating panel between the outer door deployed position and the outer door stowed position and a second thrust reverser actuator configured to pivot the inner thrust reverser door with respect to the inner articulating panel between the deployed inner door position and the stowed inner door position in order to allow independent movement of the outer thrust reverser door and the inner thrust reverser door, as taught by Madden. It has been held that combining or simple substitution of prior art elements according to known methods to yield predictable results renders the limitation obvious (see MPEP 2141 (III)). In this case, providing a first thrust reverser actuator configured to pivot the outer thrust reverser door with respect to the outer articulating panel between the outer door deployed position and the outer door stowed position and a second thrust reverser actuator configured to pivot the inner thrust reverser door with respect to the inner articulating panel between the deployed inner door position and the stowed inner door position yields predictable results.
Claim(s) 10-12 is/are rejected under 35 U.S.C. 103 as being unpatentable over US 4836451 (Herrick) in view of US 5120005 (Reedy).
Regarding claim 10-12, Herrick fails to teach a first nozzle actuator configured to pivot the outer articulating panel, a second nozzle actuator configured to pivot the forward inner skin (though unclear, construed as the inner articulating panel), and a first linear joint disposed between the first nozzle actuator and the outer articulating panel; and a second linear joint disposed between the second nozzle actuator and the forward inner skin. However, Reedy teaches a first nozzle actuator configured to pivot the outer articulating panel (first actuator 48; Fig 2-4, col 3 l. 33-col 4 l. 45), a second nozzle actuator configured to pivot the forward inner skin (second actuator 50), and a first linear joint disposed between the first nozzle actuator and the outer articulating panel (first linear joint 52 and/or 44 translates/moves linearly); and a second linear joint disposed between the second nozzle actuator and the forward inner skin (second linear joint 54 and/or 56 translates/moves linearly). It would have been obvious to one of ordinary skill in the art at the time of the invention to provide a first nozzle actuator configured to pivot the outer articulating panel, a second nozzle actuator configured to pivot the forward inner skin (though unclear, construed as the inner articulating panel), and a first linear joint disposed between the first nozzle actuator and the outer articulating panel; and a second linear joint disposed between the second nozzle actuator and the forward inner skin in order to actuate the outer articulating panel and the inner articulating panel as desired, as taught by Reedy. It has been held that combining or simple substitution of prior art elements according to known methods to yield predictable results renders the limitation obvious (see MPEP 2141 (III)). In this case, providing a first nozzle actuator configured to pivot the outer articulating panel, a second nozzle actuator configured to pivot the forward inner skin (though unclear, construed as the inner articulating panel), and a first linear joint disposed between the first nozzle actuator and the outer articulating panel; and a second linear joint disposed between the second nozzle actuator and the forward inner skin yields predictable results.
Claim(s) 15 is/are rejected under 35 U.S.C. 103 as being unpatentable over US 4836451 (Herrick) in view of US 6910328 (Joyce).
Regarding claim 15, Herrick fails to teach a flap located at a forward edge of the outer skin, wherein the flap is slidingly coupled to the outer skin to maintain a continuous aerodynamic surface while the outer articulating panel pivots. However, Joyce teaches a flap located at a forward edge of the outer skin, wherein the flap is slidingly coupled to the outer skin to maintain a continuous aerodynamic surface while the outer articulating panel pivots (Fig 3-4, flap 31 at forward edge of outer surface 19 of outer articulating panel 16). It would have been obvious to one of ordinary skill in the art at the time of the invention to provide a flap located at a forward edge of the outer skin, wherein the flap is slidingly coupled to the outer skin to maintain a continuous aerodynamic surface while the outer articulating panel pivots, as taught by Joyce (col 3 ll. 55-60).
Allowable Subject Matter
Claim 13 is objected to as being dependent upon a rejected base claim, but would be allowable if rewritten in independent form including all of the limitations of the base claim and any intervening claims and if the 112 rejection was overcome.
Conclusion


NEXT OFFICE ACTION: Notice of Pre-AIA  or AIA  Status
The present application, filed on or after March 16, 2013, is being examined under the first inventor to file provisions of the AIA .
EXAMINER’S AMENDMENT
An examiner’s amendment to the record appears below. Should the changes and/or additions be unacceptable to applicant, an amendment may be filed as provided by 37 CFR 1.312. To ensure consideration of such an amendment, it MUST be submitted no later than the payment of the issue fee.
Authorization for this examiner’s amendment was given in an interview with Trent Hoffman on 8/18/25.
IN THE CLAIMS:
1. (Currently Amended) A thrust reverser, comprising:
an outer articulating panel comprising an outer thrust reverser door pivotally coupled to the outer articulating panel, the outer thrust reverser door is movable between an outer door stowed position and an outer door deployed position with respect to the outer articulating panel to create a first opening in the outer articulating panel; and
an inner articulating panel positioned radially inward of the outer articulating panel relative to an engine central longitudinal axis and comprising an inner thrust reverser door pivotally coupled to the inner articulating panel, the inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel to create a second opening in the inner articulating panel;
wherein the inner thrust reverser door and the outer thrust reverser door are configured to redirect exhaust gasses through the second opening and the first opening in a direction having a forward component to generate reverse thrust to an aircraft.
Allowable Subject Matter
Claim 1-18 are allowed.
The following is an examiner’s statement of reasons for allowance: the prior art fails to teach, in combination with the other claim limitations, an inner articulating panel positioned radially inward of the outer articulating panel relative to an engine central longitudinal axis and comprising an inner thrust reverser door pivotally coupled to the inner articulating panel, the inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel to create a second opening in the inner articulating panel. US 4836451 teaches inner and outer articulating panels and inner and outer thrust reverser doors, but fails to teach the inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel to create a second opening in the inner articulating panel. US 4382551 teaches articulating panels and thrust reverser doors that are movable to create openings in the articulating panels, but fails to teach an inner articulating panel positioned radially inward of the outer articulating panel relative to an engine central longitudinal axis.
Any comments considered necessary by applicant must be submitted no later than the payment of the issue fee and, to avoid processing delays, should preferably accompany the issue fee.  Such submissions should be clearly labeled “Comments on Statement of Reasons for Allowance.”
Conclusion

CITED REFERENCE SUMMARIES: Ref US4836451A: Claims:
A thrust vectoring exhaust nozzle for directing a gas stream, comprising: a fixed exhaust collar having a semispherical external surface, an internal passage for conducting the gas stream therethrough, and an aftward facing discharge opening; a gimbal assembly including first and second pivots secured adjacent the spherical collar surface and defining therebetween a first gimbal axis passing through a center point defined by the collar spherical surface, and a gimbal ring, surrounding the collar and pivotally supported by the first and second gimbal pivots; third and fourth pivots defining therebetween a second common axis perpendicular to the first gimbal axis; a first clamshell having a spherical interior surface corresponding to the collar spherical exterior surface, the first clamshell secured between the third and fourth pivots and selectably pivotable about the second common axis; a second clamshell having a spherical surface corresponding to the spherical exterior surface of the fixed collar, the second clamshell also secured between the third and fourth pivot points and selectably pivotable about the second common axis; first slidable means for sealing the first clamshell to the exterior of the fixed collar; second slidable means for sealing the second clamshell to the exterior of the fixed collar; and means for selectably rotating the gimbal ring about the first gimbal axis.
a fixed exhaust collar having a semispherical external surface, an internal passage for conducting the gas stream therethrough, and an aftward facing discharge opening;
a gimbal assembly including first and second pivots secured adjacent the spherical collar surface and defining therebetween a first gimbal axis passing through a center point defined by the collar spherical surface, and a gimbal ring, surrounding the collar and pivotally supported by the first and second gimbal pivots;
third and fourth pivots defining therebetween a second common axis perpendicular to the first gimbal axis;
a first clamshell having a spherical interior surface corresponding to the collar spherical exterior surface, the first clamshell secured between the third and fourth pivots and selectably pivotable about the second common axis;
a second clamshell having a spherical surface corresponding to the spherical exterior surface of the fixed collar, the second clamshell also secured between the third and fourth pivot points and selectably pivotable about the second common axis;
first slidable means for sealing the first clamshell to the exterior of the fixed collar;
second slidable means for sealing the second clamshell to the exterior of the fixed collar; and
means for selectably rotating the gimbal ring about the first gimbal axis.
The nozzle as recited in claim 1, wherein the first and second clamshells each include a facing lip edge for defining an exhaust nozzle throat therebetween, and wherein the first and second clamshells each further include a planer stub flap secured to the respective nozzle lip of the first and second clamshells, each stub flap extending generally radially outward therefrom with respect to the spherical center point and each flap terminating in a first linear hinge oriented perpendicular to the first gimbal axis and parallel with the second common axis, a first upper divergent flap having a leading edge secured to the linear hinge of the stub flap of the first clamshell; a second lower divergent flap having a leading edge secured to the linear hinge of the stub flap of the second clamshell, and means for selectably pivoting the first and second divergent flaps about the corresponding linear hinges of the respective first and second clamshells.
a facing lip edge for defining an exhaust nozzle throat therebetween, and wherein the first and second clamshells each further include
a planer stub flap secured to the respective nozzle lip of the first and second clamshells, each stub flap extending generally radially outward therefrom with respect to the spherical center point and each flap terminating in a first linear hinge oriented perpendicular to the first gimbal axis and parallel with the second common axis,
a first upper divergent flap having a leading edge secured to the linear hinge of the stub flap of the first clamshell;
a second lower divergent flap having a leading edge secured to the linear hinge of the stub flap of the second clamshell, and
means for selectably pivoting the first and second divergent flaps about the corresponding linear hinges of the respective first and second clamshells.
The nozzle as recited in claim 1, further including: at least one reverse gas flow passage having means for regulating the flow of gas therethrough, said gas flow passage disposed between the collar internal flow passage and the exterior of the nozzle for discharging the gas stream during selected periods of desired reverse thrust.
at least one reverse gas flow passage having means for regulating the flow of gas therethrough, said gas flow passage disposed between the collar internal flow passage and the exterior of the nozzle for discharging the gas stream during selected periods of desired reverse thrust.
A thrust vectoring exhaust nozzle comprising: a fixed outlet collar having a generally rearward facing exhaust opening and a semispherical external surface defined about a center point; a gimbal ring, pivotably secured about the fixed collar and rotatable about a gimbal axis passing through the center point, the gimbal axis being oriented transversely with respect to a gas stream flowing through the outlet collar; a first clamshell having a surface corresponding to the exterior collar spherical surface; a second clamshell having a surface corresponding to the exterior collar spherical surface; the first and second clamshells being pivotably secured to the gimbal ring at second and third pivot points and independently pivotable about a common axis defined between the third and fourth pivot points, said common axis passing through the center point and oriented perpendicularly with respect to the gimbal axis and the flowing gas stream.
a fixed outlet collar having a generally rearward facing exhaust opening and a semispherical external surface defined about a center point;
a gimbal ring, pivotably secured about the fixed collar and rotatable about a gimbal axis passing through the center point, the gimbal axis being oriented transversely with respect to a gas stream flowing through the outlet collar;
a first clamshell having a surface corresponding to the exterior collar spherical surface;
a second clamshell having a surface corresponding to the exterior collar spherical surface;
the first and second clamshells being pivotably secured to the gimbal ring at second and third pivot points and independently pivotable about a common axis defined between the third and fourth pivot points, said common axis passing through the center point and oriented perpendicularly with respect to the gimbal axis and the flowing gas stream.
The nozzle as recited in claim 4, wherein: the clamshells each include a nozzle lip defining a nozzle throat thereby, and wherein the clamshells are pivotable into contact at said nozzle lips, the contacted clamshells defining a semispherical blocking structure disposed in the gas stream for substantially closing the flow of exhaust gas aftward from the nozzle, and wherein the nozzle further comprises: at least one reverse flow passage defining an alternate exhaust gas discharge path when the first and second clamshells define said blocking structure.
the clamshells each include a nozzle lip defining a nozzle throat thereby, and wherein the clamshells are pivotable into contact at said nozzle lips, the contacted clamshells defining a semispherical blocking structure disposed in the gas stream for substantially closing the flow of exhaust gas aftward from the nozzle, and wherein the nozzle further comprises:
at least one reverse flow passage defining an alternate exhaust gas discharge path when the first and second clamshells define said blocking structure.
The nozzle as recited in claim 5, wherein: the contacted clamshells define a flow blocking structure smaller than the fixed collar opening, and wherein the exhaust gas flow passes out of the nozzle via upper and lower lateral openings defined between the fixed collar and the corresponding contacted upper and lower clamshells.
the contacted clamshells define a flow blocking structure smaller than the fixed collar opening, and wherein
the exhaust gas flow passes out of the nozzle via upper and lower lateral openings defined between the fixed collar and the corresponding contacted upper and lower clamshells.
The nozzle as recited in claim 4, wherein the upper and lower clamshells each further include: a radially extending, planer stub flap secured to the nozzle lip of each clamshell, each stub flap including a linear hinge joint at the radially outward flap edge, and wherein the nozzle further comprises upper and lower divergent flaps, each flap having a leading edge secured to the linear hinge joint of the corresponding first and second clamshell stub flap, and a pair of spaced apart side walls, secured to the gimbal ring and extending aftward adjacent the stub flaps and divergent flaps and oriented generally perpendicular thereto, the stub flaps, divergent flaps, and side walls together defining a variable geometry nozzle outlet passage.
a radially extending, planer stub flap secured to the nozzle lip of each clamshell, each stub flap including a linear hinge joint at the radially outward flap edge, and wherein the nozzle further comprises
upper and lower divergent flaps, each flap having a leading edge secured to the linear hinge joint of the corresponding first and second clamshell stub flap, and
a pair of spaced apart side walls, secured to the gimbal ring and extending aftward adjacent the stub flaps and divergent flaps and oriented generally perpendicular thereto, the stub flaps, divergent flaps, and side walls together defining a variable geometry nozzle outlet passage.
Ref US6910328B1: Claims:
A vectorable variable area nozzle comprising: a pair of fixed parallel sidewalls; a pair of opposing elements which extend between the sidewalls and are mounted for rotation about a common first axis orthogonal to the sidewalls; a first actuator means for moving a first of the elements about the first axis, and a second actuator means for moving a second of the elements about the first axis, to define a convergent nozzle section; a pair of opposing flaps extending between the sidewalls downstream of the opposing elements, each of said flaps being mounted for rotation relative to an adjacent one of the elements at the downstream end of said adjacent element, a first of said flaps being mounted for rotation about a second axis orthogonal to the sidewalls and a second of said flaps being mounted for rotation about a third axis orthogonal to the sidewalls, the respective axis of rotation of each flap being situated between upstream and downstream ends of the flap; a third actuator means for moving the first of the flaps about the second axis, and a fourth actuator means for moving the second of the flaps about the third axis, to define a divergent nozzle section.
a pair of fixed parallel sidewalls;
a pair of opposing elements which extend between the sidewalls and are mounted for rotation about a common first axis orthogonal to the sidewalls;
a first actuator means for moving a first of the elements about the first axis, and a second actuator means for moving a second of the elements about the first axis, to define a convergent nozzle section;
a pair of opposing flaps extending between the sidewalls downstream of the opposing elements, each of said flaps being mounted for rotation relative to an adjacent one of the elements at the downstream end of said adjacent element, a first of said flaps being mounted for rotation about a second axis orthogonal to the sidewalls and a second of said flaps being mounted for rotation about a third axis orthogonal to the sidewalls, the respective axis of rotation of each flap being situated between upstream and downstream ends of the flap;
a third actuator means for moving the first of the flaps about the second axis, and a fourth actuator means for moving the second of the flaps about the third axis, to define a divergent nozzle section.
A vectorable variable area nozzle comprising: a pair of fixed parallel sidewalls; a pair of opposing elements which extend between the sidewalls and are mounted for rotation about a common first axis orthogonal to the sidewalls, inner faces of the opposed elements being cylindrical sections about the common first axis of rotation; a first actuator means for moving a first of the elements about the first axis, and a second actuator means for moving a second of the elements about the first axis, to define a convergent nozzle section; a pair of opposing flaps extending between the sidewalls downstream of the opposing elements, each of said flaps being mounted for rotation relative to an adjacent one of the elements at the downstream end of said adjacent element, a first of said flaps being mounted for rotation about a second axis orthogonal to the sidewalls and a second of said flaps being mounted for rotation about a third axis orthogonal to the sidewalls; a third actuator means for moving the first of the flaps about the second axis, and a fourth actuator means for moving the second of the flaps about the third axis, to define a divergent nozzle section.
a pair of opposing elements which extend between the sidewalls and are mounted for rotation about a common first axis orthogonal to the sidewalls, inner faces of the opposed elements being cylindrical sections about the common first axis of rotation;
a pair of opposing flaps extending between the sidewalls downstream of the opposing elements, each of said flaps being mounted for rotation relative to an adjacent one of the elements at the downstream end of said adjacent element, a first of said flaps being mounted for rotation about a second axis orthogonal to the sidewalls and a second of said flaps being mounted for rotation about a third axis orthogonal to the sidewalls;
A vectorable variable area nozzle comprising: a pair of fixed parallel sidewalls; a pair of opposing elements which extend between the sidewalls and are mounted for rotation about a common first axis orthogonal to the sidewalls; a first actuator means for moving a first of the elements about the first axis, and a second actuator means for moving a second of the elements about the first axis, to define a convergent nozzle section; a pair of opposing flaps extending between the sidewalls downstream of the opposing elements, each of said flaps being mounted for rotation relative to an adjacent one of the elements at the downstream end of said adjacent element, a first of said flaps being mounted for rotation about a second axis orthogonal to the sidewalls and a second of said flaps being mounted for rotation about a third axis orthogonal to the sidewalls; a third actuator means for moving the first of the flaps about the second axis, and a fourth actuator means for moving the second of the flaps about the third axis, to define a divergent nozzle section; the third actuator means being attached to the first of the elements and the fourth actuator means being attached to the second of the elements.
a third actuator means for moving the first of the flaps about the second axis, and a fourth actuator means for moving the second of the flaps about the third axis, to define a divergent nozzle section;
the third actuator means being attached to the first of the elements and the fourth actuator means being attached to the second of the elements.
A nozzle as claimed in claim 3 , wherein the second axis is fixed in relation to the first of the elements and the third axis is fixed in relation to the second of by the elements.
A nozzle as claimed in claim 3 , wherein the flaps are rotatable about their respective axes to vector thrust produced by the nozzle.
A method of vectoring a vectorable variable area nozzle, which nozzle comprises: a pair of fixed parallel sidewalls; a pair of opposing elements which extend between the sidewalls and are mounted for rotation about a common first axis orthogonal to the sidewalls; a first actuator means for moving a first of the elements about the first axis, and a second actuator means for moving a second of the elements about the first axis, to define a convergent nozzle section; a pair of opposing flaps extending between the sidewalls downstream of the opposing elements, each of said flaps being mounted for rotation relative to an adjacent one of the elements at the downstream end of said adjacent element, a first of said flaps being mounted for rotation about a second axis orthogonal to the sidewalls and a second of said flaps being mounted for rotation about a third axis orthogonal to the sidewalls, the respective axis of rotation of each flap being situtated between upstream and downstream ends of the flap; a third actuator means for moving the first of the flaps about the second axis, and a fourth actuator means for moving the second of the flaps about the third axis, to define a divergent nozzle section; said method comprising energising the first and second actuator means to rotate the first and second elements about the first axis to vector thrust produced by the nozzle independently of altering the throat area, exit area or divergence angle of the nozzle, and further comprising energising the third and fourth actuator means to rotate the first and second flaps about the second and third axes, respectively, to alter at least one of the throat area, exit area and divergence angle of the nozzle independently of vectoring the thrust produced by the nozzle.
a pair of opposing flaps extending between the sidewalls downstream of the opposing elements, each of said flaps being mounted for rotation relative to an adjacent one of the elements at the downstream end of said adjacent element, a first of said flaps being mounted for rotation about a second axis orthogonal to the sidewalls and a second of said flaps being mounted for rotation about a third axis orthogonal to the sidewalls, the respective axis of rotation of each flap being situtated between upstream and downstream ends of the flap;
said method comprising energising the first and second actuator means to rotate the first and second elements about the first axis to vector thrust produced by the nozzle independently of altering the throat area, exit area or divergence angle of the nozzle, and further comprising energising the third and fourth actuator means to rotate the first and second flaps about the second and third axes, respectively, to alter at least one of the throat area, exit area and divergence angle of the nozzle independently of vectoring the thrust produced by the nozzle.
A method as claimed in claim 6 , wherein the first and second actuator means are energised in opposing senses to rotate the first and second elements in the same sense about the first axis to vector thrust produced by the nozzle independently of altering the throat area, exit area or divergence angle of the nozzle.
A method as claimed in claim 7 , wherein the first and second actuator means are also energised in the same sense to rotate the first and second elements in opposing senses about the first axis to alter the throat area, exit area and divergence angle of the nozzle independently of vectoring the thrust produced by the nozzle.
A method as claimed in claim 8 , wherein said exit area and divergence angle are altered in one sense and said throat area is altered in an opposite sense.
A method as claimed in claim 6 , wherein the third and fourth actuator means are energised in the same sense to rotate
[Truncated to input limit]