Apparatus and method for monitoring performance characteristics of a component of a vehicle

An apparatus for monitoring at least one performance characteristic of a component of a vehicle may include a tripod connected to an exterior surface of the vehicle, the tripod includes a plurality of airfoils defining an aerodynamic surface of the tripod, a camera positioned on the tripod at a predetermined viewing angle directed toward the component of the vehicle and a camera fairing connected to the tripod and surrounding the camera, the camera fairing includes a sidewall defining an aerodynamic surface of the camera fairing, an aperture disposed through the sidewall and aligned with the camera and a plurality of protrusions positioned proximate the aperture.

FIELD

The present disclosure is generally related to monitoring performance of a vehicle and, more particularly, to an apparatus and method for visually monitoring one or more performance characteristics of a component of a vehicle, such as a wing assembly of an aircraft.

BACKGROUND

Performance testing of a vehicle is common prior to placing the vehicle into use, for example, in the aerospace industry. For example, performance characteristics of components (e.g., wing assemblies) of an aircraft need to be observed and/or recorded during flight.

Various methods are employed to monitor inflight performance characteristics. For example, a camera may be mounted inside the cabin or in the tail of the aircraft to record performance of a wing test in flight conditions. However, interior cameras often fail to provide optimum viewing angles of the desired component. As another example, to record performance of a wing test in flight conditions, a chase aircraft may carry a camera. However, cameras mounted on chase aircraft lack image stability and/or suitable image resolution. A camera mounted externally on the aircraft and displaced from tested component may provide suitable viewing angles, but experience airflow-induced vibrations that degrade resulting image quality.

Accordingly, those skilled in the art continue with research and development efforts in the field of monitoring and/or recording performance characteristics of a vehicle, such an aircraft in flight conditions.

SUMMARY

In one embodiment, the disclosed apparatus for monitoring at least one performance characteristic of a component of a vehicle may include a camera fairing defining an internal volume, the camera fairing may include a sidewall including an aerodynamic surface and an aperture disposed through the sidewall, wherein the aerodynamic surface includes a plurality of protrusions positioned proximate the aperture.

In another embodiment, the disclosed apparatus for monitoring at least one performance characteristic of a component of a vehicle may include a tripod including an aerodynamic surface, the tripod may include a first leg directed toward a forward end of the vehicle, a second leg directed toward an aft end of the vehicle, and a third leg directed toward the aft end of the vehicle, wherein each of the first leg, the second leg and the third leg are disposed at a non-zero sweep angle with respect to a plane normal to a streamline direction, wherein the third leg is offset with respect to the second leg, and wherein the second leg and the third leg are disposed at a non-zero splay angle with respect to one another.

In another embodiment, the disclosed apparatus for monitoring at least one performance characteristic of a wing assembly of an aircraft may include a tripod connected to an exterior surface of an aircraft, the tripod includes a plurality of airfoils defining an aerodynamic surface of the tripod, a camera positioned on the tripod at a predetermined viewing angle directed toward a wing assembly of the aircraft and a camera fairing connected to the tripod and surrounding the camera, the camera fairing includes a sidewall defining an aerodynamic surface of the camera fairing, an aperture disposed through the sidewall and aligned with the camera and a plurality of protrusions positioned proximate the aperture.

In yet another embodiment, also disclosed is a method for monitoring at least one performance characteristic of a wing assembly of an aircraft, the method may include the steps of: (1) connecting a tripod to an exterior surface of the aircraft, the tripod including a plurality of airfoils defining an aerodynamic surface of the tripod, (2) positioning a camera on the tripod at a predetermined viewing angle directed toward the wing assembly, (3) connecting a camera fairing to the tripod surrounding the camera, the camera fairing including a sidewall defining an aerodynamic surface of the camera fairing, an aperture disposed through the sidewall and aligned with the camera and a plurality of protrusions positioned proximate the aperture and recording at least one performance characteristic of the wing assembly during flight.

Other embodiments of the disclosed apparatus will become apparent from the following detailed description, the accompanying drawings and the appended claims.

DETAILED DESCRIPTION

The following detailed description refers to the accompanying drawings, which illustrate specific embodiments of the disclosure. Other embodiments having different structures and operations do not depart from the scope of the present disclosure. Like reference numerals may refer to the same element or component in the different drawings.

Referring toFIG. 1, the disclosed apparatus, generally designated10, for monitoring at least one performance characteristic and/or feature of a component (e.g., a wing assembly) of a vehicle (e.g., an aircraft) may include a tripod assembly12, a camera fairing14, and an imaging system16. The imaging system16may include a camera18.

The apparatus10may monitor (e.g., visually observe and/or record) one or more performance characteristics and/or features of a component20of a vehicle24. For example, the apparatus10may monitor operational performance characteristics of the vehicle24including, but not limited to, structural deflection, ice accumulation, thermal characteristics of airflow, thermal characteristics of the component20(e.g., the wing assembly) or the like. The camera18may include video camera or a still photograph camera. The camera18may obtain videos or images in the visible spectrum or the infrared spectrum.

The tripod assembly12may be connected to an exterior surface22of the vehicle24. The camera fairing14may be connected to the tripod assembly12. The camera18may be positioned within the camera fairing14. The tripod assembly12may support the camera18at a predetermined position such that a line of sight26of the camera18includes a viewing angle28with respect to a reference plane30. In the example illustrated inFIG. 1, the reference plane30may be substantially horizontal; however, those skilled in the art will appreciate that the reference plane30may have any orientation depending upon the component20being monitored.

Referring briefly toFIGS. 1 and 2, as one example, the viewing angle28and/or the reference plane30(FIG. 1) may be defined with respect to a body coordinate system132of the vehicle24(FIG. 2). For example, the body coordinate system132may include an X-axis parallel to a longitudinal axis of the vehicle24(e.g., an aircraft32) and a Y-axis normal to the X-axis (e.g., generally parallel to the wing assemblies34of the aircraft32). The horizontal reference plane30may be generally parallel to an X-Y plane defined by the X-axis and the Y-axis. A Z-axis may be normal to the X-Y plane.

Referring again toFIG. 1, the viewing angle28may be a zero angle or a non-zero angle. For example, the viewing angle28may be approximately 0 degrees. As another example, the viewing angle28may be between approximately 1 degree and 90 degrees. As another example, the viewing angle28may be between approximately 5 degrees and 60 degrees. As another example, the viewing angle28may be between approximately 15 degrees and 45 degrees. As another example, the viewing angle28may be approximately 16.8 degrees. As yet another example, the viewing angle28may be approximately 7 degrees.

Referring toFIG. 2, in an example implementation, the vehicle24may be the aircraft32and the component20may be the wing assembly34of the aircraft32. For example, the apparatus10may monitor inflight performance or simulated inflight performance (e.g., wind tunnel) of the wing assembly34.

In an example construction, the tripod assembly12may be connected to the exterior surface22of the aircraft32. For example, the tripod assembly12may be connected to an exterior surface22(e.g., an upper surface) of a fuselage37of the aircraft32approximately between the wing assemblies34. The line of sight26of the camera18may be directed toward an area of interest36(e.g., an upwardly facing surface) of the wing assembly34. For example, reference plane30(FIG. 1) may be at least partially co-planar with the upwardly facing surface of the wing assembly34.

Referring toFIG. 3, the tripod assembly12may include aerodynamic surface38and the camera fairing14may include aerodynamic surface40. The aerodynamic surfaces38,40may be suitably shaped to control and/or reduce vibrations upon the camera18and preserve image quality obtained by the camera18(FIG. 1) when monitoring the component20(FIG. 2) during operation of the vehicle24(e.g., during flight).

The tripod assembly12may include a tripod52including three legs42(identified individually as a first leg42a, a second leg42band a third leg42c). For example, the first leg42amay define a forward leg (e.g., being directed toward a forward end of the vehicle24) and the second leg42band third leg42cmay define a pair of aft legs (e.g., being directed toward an aft end of the vehicle24. As used herein, the terms forward and aft may be considered relative to a direction of movement of the vehicle24(e.g., the aircraft32).

Each leg42may include a lower end48(identified individually as lower ends48a,48band48c) and an upper end50(identified individually as upper ends50a,50band50c) longitudinally opposed from the lower end48. The lower end48of each leg42may be connected to the vehicle24. For example, the lower end48(e.g., lower ends48a,48band48c) of each leg42(e.g., the first leg42a, the second leg42band the third leg42c) may include and/or terminate at a lower attach point136connected to the exterior surface22of the vehicle24.

The first leg42amay be aligned with (e.g., directed into) a streamline direction46of the vehicle24. As used herein, the streamline direction46may be substantially opposite a direction of travel of the vehicle24. The second leg42band the third leg42cmay extend from the first leg42a. For example, the upper ends50b,50cof the second leg42band the third leg42c, respectively, may be connected to the first leg42abetween the lower end48aand the upper end50a.

The second leg42band the third leg42cmay be offset or staggered along a longitudinal axis of the first leg42a. For example, the third leg42cmay be positioned above the second leg42b. As an example, the second leg42bmay be positioned proximate (e.g., at or near) the middle of the first leg42aand the third leg42cmay be positioned proximate the upper end50aof the first leg42a.

Those skilled in the art will recognize that the position of the second leg42band the third leg42con the first leg42amay depend on the dimensions (e.g., length dimension) of the first leg42a. As a general, non-limiting example, the second leg42bmay be connected to the first leg42aat a position approximately ⅔ of the length dimension from the lower end48aand the third leg42cmay be connected to the first leg42aat a position approximately ⅚ of the length dimension from the lower end48a. As a specific, non-limiting example, the first leg42amay include a length dimension of approximately 6 feet, the second leg42bmay be connected to the first leg42aat a position approximately 4 feet from the lower end48aand the third leg42cmay be connected to the first leg42aat a position approximately 5 feet from the lower end48a.

Referring toFIG. 4, each leg42(e.g., the first leg42a, the second leg42band the third leg42c) may be disposed at a non-zero sweep angle138(identified individually as a first sweep angle138a, a second sweep angle138band a third sweep angle138c) with respect to a reference plane134normal to the streamline direction46. For example, the sweep angles138may be approximately between 40 degrees and 60 degrees. As another example, the sweep angles138may be approximately between 45 degrees and 55 degrees. As a specific, non-limiting example, the first sweep angle138amay be approximately 51.3 degrees and the second sweep angle138band third sweep angle138cmay be approximately 45.2 degrees.

The offset position of the second leg42band the third leg42cwith respect to the first leg42aand the sweep angles138of each leg42may be configured to substantially reduce and/or eliminate transonic interactions with the tripod12. As used herein, transonic may refer to a condition of flight in which a range of velocities of airflow exist surrounding and/or flowing past the legs42that are concurrently below, at, and above the speed of sound in a local Mach number range between approximately 0.5 to 1.5. As used herein, local Mach number may refer to the speed of the airflow proximate (e.g., at or around) the legs42. For example, the sweep angles138(e.g., each of the first sweep angle138a, the second sweep angle138band the third sweep angle138c) may depend upon and/or may be adjusted with respect to various factors including, but not limited to, the local Mach number and the thickness of the leg42(e.g., a cross-sectional thickness of each leg42along a Y-axis, as described herein below and illustrated inFIG. 7).

Referring toFIG. 5, each leg42may be connected to the vehicle24at a non-zero lower connection angle54with respect to the exterior surface22(identified individually as a first lower connection angle54a, a second lower connection angle54band a third lower connection angle54c). The second leg42band the third leg42cmay be connected to the first leg42aat a non-zero upper connection angle56with respect to the first leg42a(identified individually as a second upper connection angle56aand a third upper connection angle56c). Those skilled in the art will recognize that the lower connection angle54and/or the upper connection angles56may depend upon the sweep angles138.

Referring toFIG. 6, the second leg42band the third leg42cmay be disposed at a non-zero splay angle58with respect to one another. The splay angle58may depend upon the local Mach number. For example, the splay angle58between the second leg42band the third leg42cmay be set for a minimum Mach number (e.g., below 1) in order to minimize supersonic flow and avoid a wake resulting from airflow passing over the first leg42a. For example, the splay angle58may be between approximately 40 degrees and 65 degrees. As another example, the splay angle58may be approximately 60.6 degrees.

Referring toFIG. 7, in one example construction, the tripod assembly12may include an airfoil44surrounding internal support struts60defining each leg42of a tripod52. For example, each leg42may include the support strut60and the airfoil44connected to and substantially surrounding the support strut60. The airfoil44may define the aerodynamic surface38of the tripod assembly12(e.g., of each leg42). In one example construction, the aerodynamic surface38may be smooth. In another example construction, the aerodynamic surface38may include surface roughness and/or vortex generators.

The airfoil44of each leg42may include an X-axis and a Y-axis. The airfoil44of each leg42may be oriented such that the X-axis is substantially parallel to the streamline direction46. For example, the airfoil44of each leg42may be oriented such that a leading edge62of the airfoil44is aligned with and directed into the airflow. The airfoil44of each leg42may be symmetric about both the X-axis and the Y-axis. For example, the leading edge62and a trailing edge64of the airfoil44may be substantially the same (e.g., having substantially equal radius). The symmetric cross-sectional shape airfoil44may limit steady and unsteady aerodynamic side loads on the leg42(e.g., on the strut60).

Referring toFIG. 8, the support strut60may be connected to the vehicle24(e.g., at the lower end48of the leg42). A lower end68of the support strut60may be connected to the vehicle24in a non-rigid manner. The non-rigid connection between the strut60and the exterior surface22of the vehicle24(e.g., at the lower attach point136) may provide for minor movement of the strut60with respect to the exterior surface22of the vehicle24. Such minor movement of the strut60may allow for minor position adjustments of the legs42with respect to the exterior surface22of the vehicle24(e.g., the lower connection angles54), such as in response to flexing of the exterior surface22of the vehicle24(e.g., during flight of the aircraft32).

For example, the support strut60may be pivotally connected (e.g., via a pinned connection) to the vehicle24at the lower attach point136. In an example construction, the lower attach point136may include a mount fitting66connected to the exterior surface22of the vehicle24. The mount fitting66may include a tang72. The lower end68of the support strut60may include a clevis70. The tang72may be received within a U-shaped portion of the clevis70and secured by a pin.

The tripod assembly12may be grounded to the vehicle24. For example, the tripod assembly12may include a jumper cable75electrically connected between the support strut60and a grounding bracket77. The grounding bracket77may be connected to the exterior surface22of the vehicle24. The jumper cable75and the grounding bracket77may minimize or eliminate electromagnetic effects on the tripod assembly12.

Referring toFIG. 9, in one embodiment, the camera18may be connected to the upper end50aof the first leg42a. The camera fairing14may be connected to the first leg42asurrounding the camera18. For example, the camera18and the camera fairing14may be connected about the trailing edge64of the airfoil44of the first leg42a. In an example construction, the camera fairing14may include an opening78suitably sized to receive a portion of the airfoil44(e.g., a portion of the trailing edge64) of the first leg42a. The camera fairing14may include an aperture76. The aperture76may be aligned with a lens of the camera18upon the camera fairing14being connected to the first leg42of the tripod52, as further illustrated inFIG. 12.

The tripod52may include a head plate80. The head plate80may cover the upper end of the airfoil44and an upper portion of the opening78in the camera fairing14, as also illustrated inFIG. 4. The head plate80may provide an aerodynamic interface between the aerodynamic surface38of the tripod52and the aerodynamic surface40of the camera fairing14.

Referring toFIG. 10, in one embodiment, the imaging system16may include a camera enclosure82. The camera18may be mounted within the camera enclosure82. In an example construction, the camera enclosure82may include a plurality of sidewalls84defining a sealed internal volume86. The camera18may be housed within the sealed internal volume86of the camera enclosure82. The camera enclosure82may include an adjustment mechanism94interconnected with the camera18. The adjustment mechanism94may allow for rotational and/or angular position adjustment (e.g., with respect to the X-Y plane of the body coordinate system132) of the camera18within the camera enclosure82to optimally position the line of sight26of the camera18at a desired viewing angle28(FIG. 2).

In an example construction, the camera enclosure82may be connected to an upper end74of the support strut60of the first leg42a. For example, the tripod52may include a mounting bracket90connected to the upper end74of the strut60of the first leg42a. The camera enclosure82may be connected to the mounting bracket90. An interface between the camera enclosure82and the mounting bracket90may include an adjustment fastener92. The adjustment fastener92may allow for position adjustment of the camera enclosure82, and thus, the camera18, with respect to the tripod52(e.g., the strut60).

Referring toFIGS. 1 and 10, a purge system96(FIG. 2) may be connected to the camera enclosure82to maintain environmental conditions within the sealed internal volume86of the camera enclosure82to ensure image quality obtained by the camera18. For example, a dry nitrogen source98may be fluidly connected to the camera enclosure82. Tubing100may fluidly interconnect the dry nitrogen source98and the camera enclosure82. The purge system96may also include suitable valves102and/or connectors104.

The imaging system16(FIG. 2) may include a computer106communicatively connected to the camera18. The computer106may record and/or process images and/or video obtained by the camera18. Electrical cable108may electrically interconnect the computer106and the camera18. The electrical cable108may transfer power and/or data between the computer106and the camera18. The electrical cable108may include braided wire shielding to reduce or eliminate electromagnetic effects on the imaging system16(e.g., the camera18). The imaging system16may also include suitable connectors110.

Referring toFIGS. 1 and 8, in an example implementation, the dry nitrogen source98, the computer106and a suitable power supply (not shown) may be located within an interior of the vehicle24(e.g., within the aircraft32). The tubing100and the electrical cable108may extend through the exterior surface22of the vehicle24for connection to the camera enclosure82and the camera18, respectively. A grommet112may be used to seal a through hole formed through the exterior surface22through which the tubing100and the electrical cable108extend. The tubing100and the electrical cable108may pass through the grommet112connected to the exterior surface22.

Referring toFIG. 11, in an example construction, the grommet112may be suitably sized to receive two lines of tubing100(e.g., a primary tubing and a spare tubing) and two lines of electrical cable108(e.g., a primary electrical cable and a spare electrical cable). Any gaps114between the tubing100, the electrical cable108and the grommet112may be filled with a sealant116. The grommet112may include an outer ring118and a layer of over braid shielding to reduce or eliminate electromagnetic effects.

Referring toFIGS. 12-14, the camera fairing14may include a sidewall122defining an internal volume124. The sidewall122may include a curved cross-sectional profile defining the aerodynamic surface40of the camera fairing14. The aerodynamic surface40may be substantially smooth. The camera18or the camera enclosure82and the camera18may be positioned within the internal volume124, as illustrated inFIG. 12, upon the camera fairing14being connected to the first leg42a(e.g., the airfoil44) of the tripod52, as illustrated inFIGS. 13 and 14.

The opening78(FIG. 12) may be sized in close tolerance to a thickness dimension of the airfoil44of the first leg42a(FIGS. 12 and 13). Any interfaces126(FIGS. 13 and 14) between the edges of the opening78of the camera fairing14and the surface of the airfoil44may be substantially closed to provide an aerodynamic interface between the aerodynamic surface38of the airfoil44and the aerodynamic surface40of the camera fairing14. In an example construction, a sealing strip (e.g., speed tape) may be used to further cover and seal the interfaces126.

The camera fairing14may include a plurality of protrusions128extending or projecting outwardly from the sidewall122. The protrusions128may control the airflow passing over and/or into the aperture76to reduce noise (e.g., whistling and/or buzzing), vibrations, pressure variations or any other undesired signal that may negatively impact optimal image quality obtained by the camera18during monitoring of the vehicle24. The protrusions128may be positioned proximate (e.g., at or near) the aperture76. For example, the protrusions128may be positioned at least partially around the aperture76disposed through the sidewall122. The protrusions128may be aligned with streamline direction46(e.g., the direction of airflow). For example, a length dimension (e.g., length l, illustrated inFIG. 16) may be parallel with the streamline direction46.

Referring toFIG. 15, each protrusion128may include a curved cross-sectional profile (e.g., convex-shaped) having a radius R. An inter-region130of the aerodynamic surface40(e.g., an exterior surface of the sidewall122) between adjacent (e.g., side-by-side) protrusions128may include a curved cross-sectional profile (e.g., concave-shaped) opposite to the curved cross-sectional profile of the protrusions128. Thus, the plurality of protrusions128may form a wavy pattern (e.g., having a waveform) on the aerodynamic surface40.

The radius R of each protrusion128may be between approximately 0.12 inch and 0.50, and more particularly, between approximately 0.20 inch and 0.24 inch. In an example construction, the radius R of each protrusion128may be the same. In another example construction, the radius R of one or more protrusions128may be different than at least one other protrusion128. For example, an uppermost protrusion128may include the largest radius R and each successive protrusion128may include a radius R equal to or smaller than the radius R of the protrusion128directly above. As another example, a lowermost protrusion128may include the largest radius R and each successive protrusion128may include a radius R equal to or smaller than the radius R of the protrusion128directly below. As another example, the radius R each protrusion128may be different. As yet another example, the radius R of each protrusion128may be randomized.

Referring toFIG. 16, each protrusion128may gradually increase in height h as the protrusion approaches the aperture76. The height h may be between approximately 0.08 inch and 0.22 inch. In an example construction, the height h of each protrusion128may be the same. In another example construction, the height h of one or more protrusions128may be different than at least one other protrusion128. In yet another example construction, the height h of each protrusion128may be different.

Each protrusion128may include a length l as the protrusion approaches the aperture76. The length l may be between approximately 2 inches and 3 inches. In an example construction, the length l of each protrusion128may be the same. In another example construction, the length l of one or more protrusions128may be different than at least one other protrusion128. In yet another example construction, the length l of each protraction128may be different.

Accordingly, the disclosed apparatus may provide a tripod with an aerodynamic surface that positions a viewing angle of a camera to a near-optimum data collection position and controls detrimental airflow on the tripod to minimize vibrations on the camera to reduce negative impact on image quality. A camera fairing with an aerodynamic surface may surround the camera to reduce vibrations, pressure variations or any other undesirable signal to optimize image quality. In the aerospace example, the apparatus may be attached in a manner suitable to achieve system safety requirements and permit removal and/or re-installation of the tripod and/or the camera.

Referring toFIG. 17, one embodiment of a method, generally designated200, for monitoring at least one performance characteristic of a wing assembly of an aircraft may begin with the step of connecting a tripod to an exterior surface of the aircraft, as shown at block202. The tripod may include a plurality of airfoils defining an aerodynamic surface of the tripod.

As shown at block204, the camera may be mounted within a sealed internal volume of a camera enclosure and the camera enclosure may be connected to the tripod.

As shown at block206, a camera may be positioned on the tripod at a predetermined non-zero viewing angle directed toward the wing assembly.

As shown at block208, a camera fairing may be connected to the tripod surrounding the camera and/or the camera and camera enclosure combination. The camera fairing may include a sidewall defining an aerodynamic surface of the camera fairing, an aperture disposed through the sidewall and aligned with the camera and a plurality of protrusions positioned proximate (e.g., at or near) the aperture.

As shown at block210, the sealed internal volume of the camera enclosure may be purged, for example by a dry nitrogen source.

As shown at block212, at least one performance characteristic of the wing assembly may be recorded during flight of the aircraft.

Although various embodiments of the disclosed apparatus have been shown and described, modifications may occur to those skilled in the art upon reading the specification. The present application includes such modifications and is limited only by the scope of the claims.