Mechanism for a vectoring exhaust nozzle

A nozzle device defines a passageway including an outlet to discharge working fluid to produce thrust. This device includes a vectoring mechanism having three or more vanes pivotally mounted across the passageway and a linkage pivotally coupling the vanes together. This linkage includes a first arm fixed to a first one of the vanes to pivot therewith about a first pivot axis, a second arm and a third arm fixed to a second one of the vanes to pivot therewith about a second pivot axis, and a fourth arm fixed to a third one of the vanes to pivot therewith about a third pivot axis. A first connecting link pivotally couples the first arm and the second arm together, and a second connecting link pivotally couples the third arm and the fourth arm together. The relative angular positioning of the arms with respect to the corresponding pivot axes and/or the arm links can be varied to define different vectoring schedules with the mechanism linkage. In one particular form, the nozzle is utilized with a lift fan of an aircraft to perform V/STOL operations.

BACKGROUND

The present invention relates to nozzles, and more particularly, but not exclusively relates to a vectoring mechanism for a nozzle.

Aircraft thrust propulsion systems typically employ a nozzle. For some aircraft applications, it is desirable to vector thrust with the nozzle. Typically, existing vectoring schemes have relatively limited adjustability, are exceedingly complex, and/or impose a significant weight penalty. Thus, there remains a demand for further contributions in this area of technology.

SUMMARY

One embodiment of the present invention includes a unique technique to vector thrust with a nozzle. Other embodiments include unique apparatus, devices, systems, and methods involving a vectoring nozzle. Further embodiments, forms, objects, features, advantages, aspects, and benefits of the present application shall become apparent from the detailed description and drawings included herein.

DETAILED DESCRIPTION OF REPRESENTATIVE EMBODIMENTS

One embodiment of the present application includes a nozzle with a thrust vectoring mechanism. This mechanism includes at least three vanes positioned across a passageway of the nozzle, and a linkage to concurrently pivot the vanes. This linkage includes arms fixed to pivot with the vanes and connecting links pivotally interconnecting the arms. In one form, as the vanes pivot, convergence is maintained, and the throat area is changed in accordance with a desired schedule.

FIG. 1illustrates a vehicle20of another embodiment of the present invention. Vehicle20is in the form of an aircraft22, which is partially shown.FIG. 1shows a fuselage23and a cockpit24of aircraft22while parked on the ground with landing gear26deployed. In correspondence to a level, parked position;FIG. 1also displays horizontal axis H and vertical axis V relative to aircraft22. It should be appreciated that the H and V axes generally apply to a nominal level cruise mode of aircraft operation. In one form, aircraft22is of a high performance type with thrust propulsion provided by one or more gas turbine engines (not shown). An aft portion of aircraft22is not shown, being of a conventional nature such as the aircraft shown in U.S. Pat. No. 5,209,428 to Bevilaqua et al. or U.S. Pat. No. 5,769,317 to Sokhey et al., both of which are hereby incorporated by reference each in its entirety.

Aircraft22is of a Vertical/Short Take-Off and Landing (V/STOL) type. To assist with V/STOL operation, aircraft22includes a thrust vectoring system30. System30includes cavity32defined through fuselage23, which is shown in phantom. Cavity32has intake opening34and discharge passage36. System30also includes working fluid source40positioned along axis V in cavity32and vectoring nozzle device50aligned therewith to define a working fluid discharge outlet52. Source40and nozzle device50are also shown in phantom inFIG. 1. Nozzle device50is positioned in cavity32and at least partially defines discharge passage36—receiving working fluid from source40for discharge through outlet52to provide vectored thrust during V/STOL operation. The direction of flow of this working fluid is indicated by arrow W. Source40may be a lift-fan of a “cold flow” type powered through a mechanical linkage to a power source, such as one or more gas turbine engines that otherwise provide forward thrust, may be a type of gas turbine engine itself that provides a “hot flow” of working fluid, or may be differently arranged as would be known to those skilled in the art. Source40is illustrated with centerbody40a(also shown in phantom) that extends into passage36. Source40and centerbody40aeach have a generally circular cross-section taken along centerline axis C that is generally parallel to vertical axis V for the level parked position shown inFIG. 1.

System30further includes a control subsystem41. Subsystem41includes a controller42, input devices44, and actuation equipment46. Devices44include at least one pilot control44ashown in cockpit24and one or more sensors44bthat are depicted schematically. Input devices44provide corresponding input signals to controller42in a compatible signal format. Controller42monitors aircraft performance through such inputs, and selectively provides corresponding output control signals to various devices including nozzle actuation equipment46. Actuation equipment46responds to these output signals to adjust vectoring operation of nozzle device50as will be more fully explained hereinafter.

Controller42is typically positioned in an avionics bay as schematically shown inFIG. 1, and may be a single component, or a collection of operatively coupled components. When of a multi-component form, controller42may have one or more components remotely located relative to the others. Controller42may be comprised of digital circuitry, analog circuitry, or a hybrid combination of both of these types. Also, controller42may be programmable, an integrated state machine, or a hybrid combination thereof. Controller42may include one or more Arithmetic Logic Units (ALUs), Central Processing Units (CPUs), memories, limiters, oscillators, control clocks, amplifiers, signal conditioners, filters, format converters, communication ports, or the like which are not shown to preserve clarity. In one form, controller42is of a programmable variety that executes algorithms and processes data in accordance with operating logic that is defined by programming instructions (such as software or firmware). Alternatively or additionally, operating logic for controller42can be at least partially defined by hardwired logic or other hardware. In one particular form, controller42is configured to operate as a Full Authority Digital Engine Control (FADEC); however, in other embodiments it may be organized/configured in a different manner as would occur to those skilled in the art. As an addition or alternative to circuitry, controller42may include one or more electromagnetic, mechanical, hydraulic, pneumatic, or optical elements desired to interface/control devices44and equipment46. It should be appreciated that controller42may be exclusively dedicated to nozzle device control/activation, or may further be used in the regulation/control/activation of one or more other subsystems or aspects of aircraft22.

Referring additionally toFIGS. 2-5, further details regarding system30are depicted; where like reference numerals refer to like features.FIGS. 2 and 3depict nozzle device50in a perspective view with certain wall structure54being shown inFIG. 2and being removed inFIG. 3to provide comparative views. Actuation equipment46includes actuators46a,46b, and46c. Actuator46ahas a linear actuation range along axis L, and actuator46bhas a pivot range about rotational axis R. Actuator46cis of a linear type like actuator46a, but is obscured by wall structure54in the view ofFIG. 2and is partially obscured in the view ofFIG. 3. Actuators46a,46b, and46cmay each be electromagnetic, hydraulic, pneumatic, a combination of one or more of these types, or such different variety as would occur to those skilled in the art.

Wall structure54of nozzle device50defines a generally rectangular exit area for discharge outlet52, sometimes referred to as a two-dimensional (2D) nozzle type. Nozzle device50includes a vectoring mechanism60. Mechanism60includes a number of variable pitch vanes62a,62b,62c,62d,62e, and62f, (collectively designated vanes62). Vane62fis partially obscured by wall structure54inFIG. 2, being more visible inFIG. 3. The orientation of vanes62is controlled to direct the flow of working fluid as it exits outlet52. Vanes62preferably span across outlet52and are airfoil-shaped in a manner configured to provide a desired thrust efficiency and thrust directing capability. Vanes62are each pivotally mounted to wall structure54by a corresponding mounting shaft64a,64b,64c,64d,64e,64f,64g,64h(collectively referred to as shafts64). Each shaft64is journaled to aircraft22adjacent each opposing end of the corresponding vane62by a suitable pair of journal bearings within opposing wall portions54aand54bof wall structure54. Vanes62each pivot about a corresponding pivot axis66a,66b,66c,66d,66e, and66f(collectively referred to as pivot axes66). It should be understood that rotational axis R is coincident with axis66f.

Wall structure54also includes a center strut58that spans across passage36, separating each of vanes62into two generally equally sized portions. Center strut58is only shown in FIG.2—being removed as part of the wall structure54inFIG. 3. A suitable journal bearing is also provided for each of vanes62where separated by center strut58.

Thrust vectoring mechanism60further includes adjustment linkage70to adjust vanes62a,62b, and62cin concert. Adjustment linkage70includes actuation arm72fixed in relation to vane62band corresponding shaft64bto pivot together about axis66b. Actuation arm72includes a free end portion72aopposite a vane mount end portion72b. End portion72ais pivotally connected to ram76of actuator46a. In response to appropriate input signals, ram76moves in relation to body78of actuator46ato define its linear range of travel, as indicated by L. Body78is fixed to portion54aof wall structure54.

Linkage70further includes a bellcrank structure80including coupling arm82that has a free end portion82aradially extending from a vane mount portion82b. Bellcrank structure80also includes coupling arm84that has a free end portion84aradially extending from a vane mount portion84b. Arms82and84are fixed relative to arm72, shaft64band vane62bto pivot therewith about pivot axis66b.

Linkage70further includes longitudinal coupling link86with an end portion86aopposite an end portion86b, and longitudinal coupling link88with an end portion88aopposite an end portion88b. End portion86ais coupled to end portion82aof arm82to pivot about pivot axis87a. End portion88ais coupled to end portion84aof arm84to pivot about pivot axis89a. Arm82extends along a radius originating at pivot axis66bthat defines a radial segment r1from pivot axis66bto pivot axis87a. Arm84extends along a radius originating at pivot axis66bthat defines a radial segment r2from pivot axis66bto pivot axis89a. Radial segments r1and r2are specifically designated inFIG. 3, and are also shown in the diagrammatic views ofFIGS. 4 and 5to be more fully described hereinafter. Radial segments r1and r2differ in length and define an oblique angle therebetween. Correspondingly, radial segments r1and r2each define a different angle with respect to a common reference axis that is coplanar and intersects axis66b, such as axes V or H. In one preferred embodiment, r1and r2differ in length. In one more preferred embodiment, the length of r1is less than 90% of the length of r2. In an even more preferred embodiment, r1is less than 50% of the length of r2. Nonetheless, in other embodiments, the lengths of r1and r2may be approximately the same.

Linkage70further includes an arm92fixed to vane62aand shaft64ato pivot therewith about pivot axis66a, and an arm94fixed to vane62cand shaft64cto pivot therewith about pivot axis66c. Arm92has a free end portion92athat radially extends from vane mount end portion92b, and arm94has a free end portion94athat radially extends from vane mount end portion94b. End portion92aof arm92is pivotally coupled to end portion88bof link88to pivot about pivot axis89b, and end portion94aof arm94is pivotally coupled to end portion86bof link86to pivot about pivot axis87b. Arm92extends from pivot axis66ato pivot axis89bdefining radial segment r3, and arm94extends from pivot axis66cto pivot axis87bdefining radial segment r4. Radial segments r3and r4define an oblique angle therebetween if superimposed to originate at a common pivot axis.

Referring specifically toFIG. 3, mechanism60further includes linkage100that includes a bellcrank102with two arms (partially obscured). These arms are partially obscured, but may resemble arms82and84of structure80, and are fixed to pivot with vane62dand shaft64dabout pivot axis66d. The arms of bellcrank102radially extend away from pivot axis66dalong different radii, and each include a free end portion opposite a vane mount portion. This free end portion of one arm is pivotally coupled to ram108of actuator46c. Ram108has a linear range of travel relative to body110of actuator46c. Body110is fixed to wall structure54along portion54b. Linkage100also includes arm112that is fixed to pivot with vane62eand shaft64eabout pivot axis66e, and coupling link114. Arm112includes a free end portion opposite a vane mount portion. Coupling link114has end portion114aopposite end portion114b. End portion114ais pivotally coupled to the arm of bellcrank102that is not journalized to ram108, and end portion114bis pivotally coupled to the free end portion of arm112.

FIGS. 4 and 5provide a partially schematic, sectional view, in which rotational axis R, and pivot axes66,87a,87b,89a, and89bare perpendicular to the view plane, being represented by crosshairs. InFIGS. 4 and 5, like reference numerals refer to like features previously described. Also referring back toFIG. 1, nozzle device50provides an angular thrust vector range VR by changing the direction of working fluid as it exits discharge outlet52with vanes62. Different thrust vectors within this range correspond to different pivot configurations of vanes62about respective axes66. A change between different configurations results from a change in position of the movable parts of actuators46a,46b, and46c. Changing the lineal travel of actuators46aand46ccauses a corresponding change in mechanisms70and100, respectively; while rotation of actuator46bdirectly repositions vane66f.

InFIGS. 4 and 5, linkages70and100and the respective actuators46aand46care schematically shown as connected line segment patterns symbolic of corresponding kinematic chains70aand100a. Vane orientation110ais shown inFIG. 4. Vane orientation110acorresponds to one extreme of vector range VR, which is designated as vector VE1. Vane orientation110ais also depicted inFIGS. 2 and 3. Vane orientation110ais provided by the maximum length configuration of actuator46aand actuator46c, and turning vane66fto one rotational extreme with actuator46b. In contrast,FIG. 5depicts vane orientation110b. Vane orientation110bdefines an opposite extreme of vector range VR, which is designated as vector VE2. Vane orientation110bis provided by the minimum length configuration of actuator46aand actuator46c, and the rotational extreme of vane66fprovided by actuator46bopposite that in vane orientation110a.

Referring generally toFIGS. 1-5, operation of aircraft22with thrust vectoring system30is next described. During operation of thrust vectoring system30, source40provides pressurized working fluid to nozzle device50in the direction of arrow W. The pressurized working fluid continues through passage36, as at least partially defined by device50, passing between vanes62and discharging through outlet52. By pivoting vanes62in a coordinated manner, the direction of discharge of the working fluid from outlet52can be changed. As a result, the directional component of thrust (opposite the direction of the working fluid flow) may be changed. The vane pivot orientation110ashown inFIGS. 2-4provides vector VE1at one extreme of angular vector range VR, and vane pivot orientation110bshown inFIG. 5provides vector VE2at another extreme of angular vector range VR. For the depicted embodiment, vector VE1provides a nozzle vector direction of about 41 degrees relative to a 0/180 degree reference along horizontal axis H to provide vertical and aft thrust; where vertical axis V corresponds to 90/270 degrees. Vector VE2provides a nozzle vector direction of about 104 degrees relative to horizontal axis H to provide vertical and slightly forward thrust. Accordingly, a vector range VR spans about 63 degrees in this embodiment; however, it should be appreciated that other embodiments may have a different range with one or more different extremes.

Vane pivot orientations110aand110bcorrespond to opposite extremes of actuators46a,46b, and46c. Accordingly, vectors between vector VE1and vector VE2are provided by corresponding intermediate positions of actuators46a,46b, and46c. It should be appreciated that as actuators46a,46b, and46cmove, vanes62each pivot about respective pivot axes66by different angular amounts as determined by actuator movement and the correspondingly coupled linkages70and100. For the depicted form, vanes62are configured to maintain converging passageways between them throughout the vectoring range VR. In other implementations, vanes62may be configured so that two or more vanes62turn substantially the same angular amount over some or all of the angular thrust vector range VR and/or convergence of some or all of the passageways between vanes62may not be maintained over some or all of the angular thrust vector range VR.

In addition to providing a thrust vector range, it is often desirable to control throat area over that range. Typically, throat area control requires that one or more of vanes62pivot by a different amount relative to the others as in the case of the depicted embodiment. The two vane orientations110aand110bshown inFIGS. 4 and 5provide one nonlimiting illustration of different degrees of pivoting from one vane40to the next to provide a selected throat area schedule during thrust vectoring. Such scheduling may include a predefined change in throat area as thrust vector direction changes. Nozzle throat area control may be performed in terms of various different parameters, including but not limited to geometric throat area, effective throat area, and discharge coefficient of the nozzle to name just a few. It should be understood that changes in effective throat area may not be uniform with respect to changes in the geometric throat area of the nozzle. As used herein, the “discharge coefficient” of a nozzle refers to the ratio between actual mass flow through the nozzle and the ideal or theoretically attainable fluid mass flow through the nozzle. For practical nozzle designs, the discharge coefficient is generally less than one (<1) due to the formation of boundary layers and other non-ideal conditions. The “geometric throat area” of a nozzle refers to the measured throat area of the nozzle configuration. The “effective throat area” of a nozzle refers to a nozzle area that is required to attain a desired actual mass flow rate through a given nozzle configuration and is defined by the expression:
effective throat area=(AFR/IFR)*GTA;
where AFR=actual flow rate, IFR=ideal or theoretically attainable flow rate, and GTA=geometric throat area of the nozzle. The term (AFR/IFR) is the discharge coefficient for the given nozzle. For a discharge coefficient less than one (<1), the effective throat area is less than the geometric throat area. Maintaining a generally constant geometric throat area while discharge coefficient varies with changes in vane orientation, typically results in a change in thrust vector magnitude for a constant level of working fluid supplied to the nozzle. In contrast, a generally constant effective throat area accounts for discharge coefficient changes and results in an approximately constant thrust magnitude for a constant level of working fluid supplied to the nozzle.

In one embodiment of the present invention, an approximately constant effective throat area is maintained to accommodate changes in discharge coefficient over a given profile of nozzle performance. In another embodiment, an approximately constant geometric throat area is provided. In still another embodiment, a throat area schedule is provided as a function of the discharge coefficient that may not maintain a generally constant geometric or effective throat area. In yet other embodiments, a different throat area control arrangement may be utilized as would occur to those skilled in the art or throat area control may not be desired at all.

It should be understood that the concurrent pivoting of vanes62a-62cwith different relative amounts of angular turning is determined by the kinematics of linkage70. For linkage70, differences in length and angular spacing of arms72,82,84,92, and94, and the length of coupling links86,88, and114between pivot connections of the respective arms define a particular schedule of vector and throat area. Linkage100operates in a similar manner, but involves fewer vanes (vanes62dand62e). In one alternative embodiment, a single linear actuator is used in lieu of actuator46aand46cwith appropriate mechanical coupling between linkages70and100.

Because vane62fis the only vane configured to rotate in response to actuator46b, it can be controlled independent of the others. As a result, vane62fcan be used to trim the throat area to a desired schedule otherwise provided with vanes62a-62eover the pivoting range. This trimming vane arrangement may be used to accommodate nonlinear changes that may be more awkward to address with mechanical linkage. Nonetheless, in other embodiments, more or fewer independently pivotable vanes can be included for trimming or other desired application. Additionally or alternatively, coupling to other linkage can be used to rotate vane66fwith actuator46aor actuator46cinstead of actuator46b.

Controller42can be arranged to generate one or more thrust control output signals to control actuators46a-46cand correspondingly provide a desired vane orientation. The output signals can be a function of one or more steering signals from control44a, one or more sensor signals from sensors44b, or a combination of these. For instance, controller42can provide one or more actuator output signals in response to such signals to provide a stable hover mode of operation; direct aircraft22along a desired heading; initiate V/STOVL operation; and/or provide a smooth transition between cruise and V/STOVL operating modes. Examples of sensor-based signals to which controller42could be responsive include rate of travel; degree to which the aircraft is level, such as pitch and roll position of the aircraft; acceleration; weight; balance; threat avoidance; weight-on-wheels, and such other aircraft parameters as would occur to those skilled in the art.

Many other embodiments of the present invention are envisioned. For example, thrust vectoring mechanisms of the present invention are provided for a passage through a different part of an aircraft in another embodiment, which correspondingly changes its vectoring characteristics. For instance, vectoring mechanisms of the present invention may be applied to an axial discharge nozzle utilized to propel an aircraft during cruise mode operation. This alternative nozzle embodiment may or may not include a turning hood to facilitate V/STOVL operation. Moreover, the teachings of the present invention may be utilized in aircraft other than V/STOVL types. In further examples, the number of vanes can be more or fewer, and/or vanes can be utilized in combination with other working fluid directing techniques as are known to those skilled in the art. In one alternative utilizing a working fluid at high temperature, a mixer/ejector is also incorporated into the thrust vectoring nozzle.

A further example of the present invention includes a nozzle device defining a passageway that has an outlet to discharge working fluid to produce thrust. This device also includes a vectoring mechanism having three vanes pivotally mounted across the passageway and a linkage. This linkage includes a first arm fixed to a first one of the vanes to pivot therewith about a first pivot axis, a second arm and a third arm fixed relative to one another and to a second one of the vanes to pivot therewith about a second pivot axis, a fourth arm fixed to a third one of the vanes to pivot therewith about a third pivot axis. The linkage also includes a first connecting link pivotally coupled to the first arm and the second arm and a second connecting link pivotally coupled to the third arm and the fourth arm. The second arm extends along a first radial axis and the third arm extends along a second radial axis. The first and second radial axes are each perpendicular to the second pivot axis and intersect the second pivot axis at a common point to form a desired angle therebetween. An actuator engages the linkage that is responsive to one or more input signals to cause the vanes to rotate together in accordance with a desired schedule.

Another example comprises: discharging working fluid through a passageway of a nozzle to produce thrust that includes three or more vanes pivotally mounted across the passageway in a linkage pivotally interconnecting the vanes, pivoting the vanes together over a range of travel to provide different thrust vectors with each of the vanes turning a different angular amount over the range of travel, and changing nozzle throat area defined with the vanes while maintaining a convergent relationship between the vanes during the pivoting of the vanes over the range of travel. In one form, the linkage includes a first arm fixed to the first one of the vanes to pivot therewith, a second arm and a third arm fixed to a second one of the vanes to pivot therewith, and a fourth arm fixed to a third one of the vanes to pivot therewith. Also included can be a first connecting link journaled to the first arm and the second arm and a second connecting link journaled to the third arm and the fourth arm.

Yet another example includes an aircraft. This aircraft comprises a thrust mechanism including means for discharging working fluid through a passageway of a nozzle to produce thrust that includes three or more vanes pivotally mounted thereacross, means for pivoting the vanes together over a range of travel to provide different thrust vectors with each of the vanes turning a different angular amount over the range of travel, and means for changing nozzle throat area defined with the vanes while maintaining a convergent relationship between the vanes during the pivoting of the vanes over the range of travel. In one form, the linkage interconnecting the vanes includes a first arm fixed to a first one of the vanes to pivot therewith, a second arm and a third arm fixed to a second one of the vanes to pivot therewith, and a fourth arm fixed to a third one of the vanes to pivot therewith.

Still another example includes: a nozzle device defining a passageway having an outlet to discharge working fluid to produce thrust. This device further includes a vectoring mechanism with three vanes pivotally mounted across the passageway and a linkage pivotally coupling the vanes together. This linkage includes a first arm fixed to a first one of the vanes to pivot therewith about a first pivot axis, a second arm and a third arm fixed to a second one of the vanes to pivot therewith about a second pivot axis, and a fourth arm fixed to a third one of the vanes to pivot therewith about a third pivot axis. Also included in the linkage is a first connecting link coupled to the first arm to pivot about a first pivot point and the second arm to pivot about a second pivot point, and a second connecting link coupled to the third arm to pivot about a third pivot point and the fourth arm to pivot about a fourth pivot point. In one nonlimiting form, a first radial segment extends from the first pivot axis to the first pivot point and forms a first angle with a first vertical reference axis intersecting the first pivot axis. A second radial segment extends a first distance from the second pivot axis to the second pivot point and the third radial segment extends a second distance from the second pivot axis to the third pivot point. This second distance is less than about 90% of the first distance. A fourth radial segment extends from the fourth pivot axis to the fourth pivot point and forms a second angle with a second vertical reference axis intersecting the third pivot axis. This second angle differs from the first angle by at least about 10 degrees. Nonetheless, in other embodiments, the angular difference and/or the difference in distances can vary as would occur to those skilled in the art.

In a further example, an apparatus comprises a nozzle device defining a passageway with an outlet to discharge a working fluid to produce thrust. The nozzle device includes a vectoring mechanism that has a first vane mounted across the passageway to pivot about a first pivot axis, and a bellcrank fixed to the first vane to pivot therewith about the first pivot axis. The bellcrank includes a first arm extending along a first radial axis from the first pivot axis to a first free end portion and a second arm extending along a second radial axis from the first pivot axis to a second free end portion. The first radial axis and the second radial axis are each perpendicular to the first pivot axis and intersect the first pivot axis. The first arm and the second arm are fixed in relation to one another to define a fixed angle between the first radial axis and the second radial axis. Also included is a second vane mounted across the passageway to pivot about a second pivot axis, and a first linkage including a first arm link fixed to the second vane to pivot therewith about the second pivot axis, and a first connecting link. The first arm link extends from the second pivot axis to a first connector engagement portion. The first connecting link is pivotally connected to the first connector engagement portion and the first free end portion of the first arm. Furthermore, this example includes a third vane mounted across the passageway to pivot about a third pivot axis, and a second linkage including a second arm link fixed to the third vane to pivot therewith about the third pivot axis, and a second connecting link. The second arm link extends from the third pivot axis to a second connector engagement portion. The second connecting link is pivotally connected to the second connector engagement portion and the second free end portion of the second arm.

Still a further example is directed to a nozzle device defining a passageway with an outlet to discharge a working fluid to produce thrust. The nozzle device includes a vectoring mechanism that has three vanes pivotally mounted across the passageway and linkage pivotally coupling the vanes together. The linkage includes: a bellcrank fixed to a first one of the vanes to pivot therewith about a first pivot axis. The bellcrank includes a first arm extending along a first radius perpendicular to the first pivot axis and a second arm extending along a second radius perpendicular to the first pivot axis. The first radius and the second radius each intersect the first pivot axis. The first arm and the second arm are fixed in relation to one another. A first arm link is fixed to a second one of the vanes to pivot therewith about a second pivot axis and a first connecting link is pivotally connected to the first arm link and the first arm. A second arm link is fixed to a third one of the vanes to pivot therewith about a third pivot axis, and a second connecting link is pivotally connected to the second arm link and the second arm. An actuator is engaged to the linkage that is responsive to one or more input signals to cause the vanes to rotate together in accordance with a desired schedule.

Any theory, mechanism of operation, proof, or finding stated herein is meant to further enhance understanding of the present invention and is not intended to make the present invention in any way dependent upon such theory, mechanism of operation, proof, or finding. It should be understood that while the use of the word preferable, preferably or preferred in the description above indicates that the feature so described may be more desirable, it nonetheless may not be necessary and embodiments lacking the same may be contemplated as within the scope of the invention, that scope being defined by the claims that follow. In reading the claims it is intended that when words such as “a,” “an,” “at least one,” “at least a portion” are used there is no intention to limit the claim to only one item unless specifically stated to the contrary in the claim. Further, when the language “at least a portion” and/or “a portion” is used the item may include a portion and/or the entire item unless specifically stated to the contrary. While the invention has been illustrated and described in detail in the drawings and foregoing description, the same is to be considered as illustrative and not restrictive in character, it being understood that only the selected embodiments have been shown and described and that all changes, modifications and equivalents that come within the spirit of the invention as defined herein or by any of the following claims are desired to be protected.