NL2018888B1

NL2018888B1 - Acoustic paneling

Info

Publication number: NL2018888B1
Application number: NL2018888A
Authority: NL
Inventors: Herrera Eric; Baginska Elleby Marta; Duschl Garry
Original assignee: Boeing Co
Priority date: 2017-05-10
Filing date: 2017-05-10
Publication date: 2018-11-15

Abstract

Systems and methods are provided for acoustic paneling. One embodiment is a method for fabricating an acoustic panel. The method includes receiving a sheet of thermoplastic paper, stamping/conforming the sheet into rows that each comprise a three dimensional shape, and transforming the sheet into a multi-celled core. Transforming the sheet includes identifying fold lines separating the rows, folding the sheet at the fold lines in a pleat fold, thereby uniting upper surfaces of adjacent rows and uniting lower surfaces of adjacent rows, and compressing the rows of the folded sheet together in the presence of heat, causing adjacent rows to fuse together into cells. The method further includes applying a backing sheet to the core, and applying a facesheet to a surface of the core that includes openings which direct a portion of airflow across the facesheet into the cells, resulting in acoustic control.

Description

ACOUSTIC PANELING

Field

The disclosure relates to the field of acoustic control, and in parti cular, to panels that provide acoustic control such as sound damping/attenuating as a function of frequency.

Background

Aircraft engines produce a great deal of noise du ring takeoff, flight, and landing. In order to increase passenger comfort and provide a more pleasant experience during flight, acoustic paneling may be provided that dampens and/or redirects noise from the engines during takeoff, flight, and landing. Acoustic paneling within an aircraft may further be utilized to reduce/redirect aircraft noise away from bystanders that may be proximate to the aircraft during takeoff and landing.

Acoustic panel ing may comprise a structure specifically designed to absorb or reflect sound away from a sensitive area. Ideally, acoustic paneling for an aircraft would be sufficient to completely absorb noise perceived by passengers from engines and other components. However, such an amount of acoustic paneling for an aircraft would be very heavy and/or occupy a substantial amount of space within the aircraft,, which in turn increases the expense of transporting passengers. Furthermore, acoustic paneling is often painstakingly assembled cell by cell in order to conform to the complex geometries of an aircraft. Such labor intensive processes further increase the expense of manufactu ring the aircraft, and are therefore undesirable. Hence, designers of aircraft carefully balance concerns of comfort and cost when add ing acoustic paneling to an aircraft.

Summary

The disclosure relates to techniques and automated manufacturing processes that transform sheets of thermoplastic material into multi-celled acoustic paneling for an aircraft. Specifically, the disclosure relates to the folding, skimping, and/or extrusion of a planar sheet of thermoplastic material to form a multi-ceiled core of an acoustic panel. A facesheet with multiple openings is applied over the cells of the core in order to form the cells into acoustic chambers (eg., for damping/attenuating one or more frequencies of sound). Using this fabrication technique, the speed of creating the acoustic panel may be beneficially increased, and costs may be reduced. The acoustic panels discussed herein provide a further benefit because they are capable of undergoing plastic deformation (e.g., via the application of heat and pressure) in order to conform to complex surfaces within an aircraft (e.g., an engine cowling).

The disclosure also relates to an apparatus comprising an acoustic panel. Tire acoustic panel includes a core comprising multiple cells of thermoplastic having walls that are fused together. The panel also includes a facesheet fused to a surface of the core. The facesheet includes multiple openings through which sound waves enter the cells, resulting in acoustic control.

The disclosure also relates to a method for fabricating the acoustic panel. The method includes receiving a sheet of thermopla stic paper, conforming the sheet into rows that each comprise a three dimensional shape, and transforming the sheet into a multi-celled core. Transforming the sheet includes identifying fold lines separating the rows, folding the sheet at the fold lines in a pleat fold, thereby uniting upper surfaces of adjacent rows and uniting lower surfaces of adjacent rows; and compressing the rows of the folded sheet together in the presence of heat, causing adjacent rows to fuse together into cells. The method further includes applying a backing sheet to the core, and applying a facesheet to a surface of the core that includes openings which direct a portion of airflow' across the facesheet into the cells, resulting in acoustic control.

The disclosure also relates to a method for performing acoustic control of jet engine noise using the acoustic panel. The method includes receiving airflow across openings of a facesheet of the panel that is fused to a multi-celled core of the panel, and directing the airflow into cells of the acoustic panel via the openings in the facesheet. The method also includes absorbing energy from the airflow' as the airflow travels within the cells such that audible frequencies of sound generated by the airflow are attenuated by the cells, reflecting the airflow off of a backing sheet for the cells, and expelling the airflow from the cells via the facesheet.

The disclosure also relates to the provision of techniques and automated manufacturing processes that utilize (e g., thermoplastic) material to mass fabricate multi-celled acoustic paneling for aircraft. Specifically, the disclosure enables acoustic paneling to be automatically fabricated via three dimensional (3D) printing and/or Automated Fiber Placement (AFP) techniques. A thermoplastic facesheet with porous sections is applied over a core of acoustic cells, and portions of the facesheet are fused into place onto the cells via a laser. Using this fa brication techn ique, the speed of creating the acoustic panel may be beneficially increased, and costs may be reduced. The acoustic panels discussed herein provide a further benefit because they are capable of undergoing plastic deformation (e.g., via the application of localized heat and pressure) in order to conform to complex surfaces within an aircraft (e g., an engine cowling), even after fabrication is complete.

The disclosure also relates to a method comprising acqui ring a core of acoustic cells,and fabricating a facesheet covering the core by: dispensing a base layer of material atop the acoustic cells while leaving openings into each of the acoustic cells, covering the openings by applying a liner of porous material atop the base layer, dispensing a cap layer of material atop liner while leaving gaps in the cap layer over the acoustic cells, and fusing the cap layer to the liner by directly radiating laser energy onto locations where the cap layer has been dispensed.

The disclosure also relates to a non-transitory computer readable medium embodying programmed instructions which, when executed by a processor, are operable for performing a method. The method includes acqui ring a core of acoustic cells, and fabricating a facesheet covering the core by: dispensing a base layer of material atop the acoustic cells while leaving openings into each of the acoustic cells, covering the openings by applying a liner of material atop tire base layer, dispensing a cap layer atop the liner while leaving gaps in the cap layer over the acoustic ceils, and fusing the cap layer to the liner by directly radiating laser energy onto locations where the cap layer has been dispensed.

The disclosure also relates to a system that includes an Automated Fiber Placement (AFP; machine. The AFP machine includes a kinematic chain of actuators and rigid bodies, and an end effector. The end effector includes a dispenser that dispenses material, and a laser that radiates laser energy which fuses the material. The AFP machine further includes a controller that operates the end effector to operate in accordance w ith instructions in a Numerical Control (NC) program that directs the AFP machine to acquire a core of acoustic cells, and fabricates a facesheet covering die core by: dispensing a base layer of material atop the acoustic cells while leaving openings into each of the acoustic cells, covering the openings by applying a liner of porous material atop the base layer, dispense a cap layer of material atop the liner while leaving gaps in the liner over the acoustic cells, and fuse the cap layer to the liner by directly radiating laser energy onto locations where the cap layer has been dispensed.

The disclosure also relates to a method for performing acoustic control of jet engine noise via an acoustic panel. The method includes receiving airflow across openings of a facesheet of the panel, maintaining laminar airflow across the openings, directing the airflow into cells of the acoustic panel via the openings in the facesheet through a porous liner, absorbing energy from the airflow as the airflow travels within the cells.

The disclosure also relates to an apparatus comprising the acoustic panel. The panel includes a core comprising multiple cells having walls that are fused together, and a facesheet including multiple openings through which sound waves enter the ceils, and a porous liner in the openings.

The disclosure also relates to a method for performing acoustic control of jet engine noise via the acoustic panel. The method includes receiving airflow across openings of a facesheet of the panel, arranging each of the openings with respect to airflow7 such that a dimension of the opening parallel to airflow7 is smaller than a dimension of the opening perpendicular to airflow7, di recting the airflow into cells of the acoustic panel via the openings in the facesheet through a porous liner, and absorbing energy from the airflow as the airflow travels within the cells.

Description of the Drawings

The present invention is now described, with reference to the accompanying drawings. The same reference number represents the same element or the same type of element on all drawings. FIG. 1 is a diagram of an aircraft. FIG. 2 is a diagram illustrating an engine of an aircraft. FIGS. 3-9 are diagrams illustrating a multi-celled acoustic panel. FIGS. 10-12 are diagrams illustrating a facesheet of an acoustic panel. FIGS. 13-14 are cross-sections illustrating components of an acoustic panel. FIG. 15 is a circuit diagram illustrating acoustic control. FIG. 16 is a flowchart illustrating a method for fabricating an acoustic panel. FIG . 17 is a flowchart illustrating a method for utilizing an acoustic panel. FIG . 18 is a block diagram of an engine utilizing an acoustic panel. FIG. 19 is a flow diagram of aircraft production and sen ice methodology. FIG. 20 is a block diagram of an aircraft. FIGS. 21-22 are diagrams illustrating a multi-celled acoustic panel. FIG. 23 is a diagram illustrating a system for fabricating acoustic paneling. FIG. 24 is a top view of completed acoustic paneling. FIG. 25 is atop view a further acoustic paneling. FIG. 26A is a flowchart illustrating a method for acoustic control. FIG. 26B is a flowchart illustrating a method for fabricating acoustic paneling. FIG. 27 is a block diagram of installed acoustic paneling. FIG. 28 is a block diagram of a fabrication system for acoustic paneling.

Description FIGS. 1 -2 illustrate environments that may benefit from enhanced acoustic control. Specifically, FIG. 1 is a diagram of an aircraft 100. Aircraft 100 includes nose 110, wings 120, fuselage 130, tail 140, and engine 150 (e.g., a turbofan jet engine that generates noise perceptible to passengers). FIG. 1 also illustrates a downward direction (Z) for aircraft 100. FIG. 2 is a d iagram of aircraft engine 150 indicated by view arrows 2 of FIG . 1. Engine 150 includes inlet 152 through which airflow 155 travels. Engine cowling 154 surrounds inlet 152, fan blades 156, compression section 157, and combustion section 158. As airflow 155 enters inlet 152 (e.g., during takeoff, flight, and landing), a substantial amount of noise is generated. This noise generated by inlet 152 may be audible to passengers inside of aircraft 100 at a level of volume that is undesirable. In order to control this noise, acoustic panel 200 is placed within inlet 152 such that sound waves within inlet 152 will be subject to control/damping/attenuation by acoustic panel 200. Hus beneficially increases passenger comfort.

Further details of the features of acoustic panel 200 are described with regard to FIGS. 3-9. Specifically, FIGS. 3-4 illustrate a fully fabricated acoustic panel 200, while FIGS. 5-9 illustrate a fabrication process for creating a hexagonal “honeycomb” core of cells for panel 200. FIG. 3 is an underside view of panel 200 that illustrates a view of a face 202 of panel 200 indicated by view arrows 3 of FIG. 2. As shown in FIG. 3, the underside of acoustic panel 200 includes openings 204 through which airflow may enter and/or exit panel 200 for acoustic control. FIG. 4 illustrates a section cut view of a side of acoustic panel 200 illustrated by view arrows 4 of FIG. 3. FIG. 4 illustrates that panel 200 includes a core 206 which includes cells 240 defined by borders/walls 230. Each cell 240 in panel 200 is sandwiched between (i.e., encapsulated by) a facesheet 210 and a backing sheet 220. Facesheet 210 is exposed to airflow 155 across panel 200. Furthermore, as shown in FIG. 4. openings 204 allow sound w ave s/vi brations from airflow 155 to enter cells 240. These sound waves from airflow 155 may then be attenuated by travel within cells 240 and/or reflection off of backing sheet 220 (as will be illustrated in later FIGS. Further discussion of acoustic panel 200 in FIGS. 5-9 focuses upon the fabrication of acoustic panel 200. The fabrication techniques discussed herein beneficially forego traditional techniques of manually creating each cell of an acoustic panel. FIG. 5 illustrates that in order to form core 206 of cells 240, a sheet 500 of thermoplastic paper (eg., Poly Ether Ether Ketone (PEEK.)) may first be acquired. Sheet 500 is stamped and folded by machinery' into individual rows 620 (e.g., row 622, row 624, row 626. etc.). As shown in FIG. 6, after stamping/confonning has been completed, each row 620 defines a three dimensional (3D) shape 650, w hich in this case is a series of half-hexagons show n in FIG. 7. Individual rows are mirrored with respect to their neighboring/adjacent rows. For example, row 624 is mirrored with respect to row 622 along fold line 630, and row 624 is further mirrored with respect to row 626 along fold line 640. When row s 622, 624, and 626 are folded together, upper surface 621 of row' 622 is mated against upper surface 623 of row 624. Furthermore, lower surface 625 of row' 624 is mated w ith lower su rface 627 of row 626. When rows 620 are pressed against their neighbors via the application of sufficient heat and/or pressure, the mated surfaces (e g., 621 and 623, 625 and 627) of these rows fuse together to form an integral, single seamless piece of thermoplastic. The process of stamping and/or folding sheet 500 into core 206 is shown to progress over time from left to right as indicated by regions 610, 612, 614, 616, and 618 of FIG. 6. Thus, core 206 may be formed from a single sheet 500 of thermoplastic . FIG. 7 illustrates a view of an individual row 620. Specifically, the view of FIG. 7 is indicated by view arrows 7 of FIG. 6. As show n in FIG. 7, the three dimensional shape 650 defining each row 620 may include a series of walls 230 that form trapezoids, half hexagons, or any suitable shape (e.g., half-circles, “C” patterns, etc.). In this manner, when rows 620 are folded together, walls 230 may unite to form hexagonal cells 240 shown in FIG. 8. FIG. 8 further illustrates that each row· 620 may form half of a hexagonal cell 240. FIG. 9 illustrates a zoomed in view of a cell 240 corresponding to region 9 of FIG. 8. FIG. 9 makes clear that in the folded and stamped configuration, each hexagonal cell 240 may include multiple walls 230 defining a single side, as shown in region 910. This could potentially present a problem by enabling sound waves to travel between cells 920 and 930, which is undesirable because it inhibits the ability of these cells to perform acoustic control of specific frequencies of sound. This problem may be addressed by heating core 206 and pressing walls 230 together in region 910 (e.g., as part of the fold-stamping process), resulting in walls 230 plastically deforming and integrating into each other to create core 206 as a singly integral shape comprising unified, seamless walls 230 of thermoplastic material.

The techniques shown in FIGS. 5-9 are vastly beneficial, because they enable the automated creation of vast quantities of cells for acoustic panels. This substantially reduces labor costs involved in producing acoustic panels. FIGS. 10-12 are diagrams illustrating application of a facesheet onto core 206 in order to form an acoustic panel. . As shown in FIG. 10, facesheet 210 is disposed onto core 206, at surface 241 defined by cells 240. Facesheet 210 includes perforations 1020 and/or open interstices over each cell 240 in order to enable sound waves to enter cells 240 as airflow 155 rushes across panel 200. Facesheet 210 may be applied, for example, via a roller 1010. Where facesheet 210 comprises a thermoplastic, facesheet 210 may be structurally united/fused with cells 240 via the application of heat and pressure at roller 1010, causing facesheet 210 and cells 240 to form a single integral seamless whole of the same thermoplastic material. Facesheet 210 performs a substantially beneficial role for acoustic panel 200. because facesheet 210 defines a resistance of each cell 240 to receiving (and/or releasing) a sound wave. By calibrating this property of facesheet 210 to ensure that some, but not all airflow 155 may enter a cell 240, acoustic control (e.g., sound dampening) may be beneficially achieved by panel 200. FIG . 11 illustrates facesheet 210 comprising a woven linear layer 1100. Layer 1100 includes an open weave 1102 of material formed from linear segments (1110, 1120, 1130) of thermoplastic. Here, the open weave 1102 may comprise any suitable weave that leaves open interstices 1140 between the linear segments (1110, 1120, 1130). The weave may further comprise a square weave, hexagonal weave, etc. Furthermore, the weave may be quantified by a “Percent Open Area” (POA) indicating a percentage of total area of the weave that is occupied by open interstices (i.e., instead of linear segments). It may be desirable to ensure that the POA and interstice sizes are selected such that each cell 240 receives sound energy directly via at least one interstice 1140. , Weave 1102 may define multiple types of interstices 1140 of different sizes and/or shapes.

As shown in FIG. 12, facesheet 210 may comprise a layer of thermoplastic 1210 (e.g., of about 1 millimeter in thickness), which includes multiple perforations, openings, and/or slots 1240. Slots 1240 are elongated in an expected direction of airflow 155. That is, the longest dimension of slots 1240 (L) is measured in the direction of expected ai rflow 155, and airflow 155 enters cells 240 via slots 1240. FIGS. 13-14 are cross-sections illustrating components of an acoustic panel 200. . hi FIG. 13, facesheet 210 preferably includes two perforated thermoplastic sheets 1200, and woven linear layer 1100. One of sheets 1200 is in contact with surface 241 of cells 240, and layer 1100 is in contact with both sheets 1200 (i.e., because it is sandwiched between both sheets). Airflow 1310 causes soundwaves to enter cell 240, reflect off of backing sheet 220. A septum 1320 of sound absorbing material (e.g., flexible foam) can be included within each cell 240, to further facilitate the damping/attenuation and/or control of sound. Here,, airflow 1310 is directed through septum 1320 prior to reflecting off of backing sheet 220. FIG. 14 i llustrates a fu rther variation of an acoustic panel 200. In FIG. 14, facesheet 210 comprises a linear woven layer 1100 in contact with cells 240, and a perforated thermoplastic sheet 1200 forming a layer in contact with layer 1100.

The arrangement of materials and structure described above enables a designer to programmatically design acoustic panels 200 in a manner that specifically absorbs sound at desired frequencies. By way of analogy, each cell 240 in panel 200 may be equated to a circuit that includes a resistor, inductor, and capacitor (an RLC circuit). Sound level may be equated to voltage, mass flow of air into a cell 240 may be equated to amperage, and so on. The amount of sound attenuated for specific frequencies (e.g., the frequency response of the RLC circuit) may be controlled by adjusting various physical parameters pertaining to the cell 240.

Utilizing the circuit diagram 1500 of FIG. 15, an impedance of an entire acoustic panel can be calibrated. R1 and R2 represent resistors of the RLC circuit of FIG. 15, Cl and C2 represent capacitors of the RLC circuit of FIG. 15, and LI represents an inductor of the RLC circuit. From these features, Zl, Z2, and Z system (representing impedance of various portions of the circuit) may be calculated. Specifically, R1 corresponds to a resistance/damping of acoustic energy provided by a facesheet of tire panel. LI corresponds to impedance of air flow caused by the shape, number, and/or size of openings in the facesheet (and may, for example, be calibrated by adjusting POA for the facesheet). Continuing onward, CT corresponds to a volume of air between a septum and the facesheet, while C2 corresponds to a volume of air between the septum and a backing sheet. R2 is defined by resistance/damping of acoustic energy caused by travel through the septum. Z1 may be calibrated by varying Rl, LI, and Cl as desired. In a similar fashion, Z2 may be calibrated based on values for R2 and C2. In this manner, Zsystem for the entirety of the acoustic panel may rapidly be calculated. For example, the POA of facesheet 210 may be chosen to provide a specific level of resistance to ai rflow into cell 240 that dampens a selected frequency of audible sound. Meanwhile, the thickness of facesheet 210 may provide an i nductive response that regulates mass flow of air into cell 240. A septum 1320 within cell 240 may define capacitance (energy storage) of the cell, and further may resist airflow. Thus, volumes of free space within cell 240. as well as the total volume of cell 240 may be considered and programmatically controlled in a double Degree of Freedom (DOF) system in order to control the acoustic properties of cell 240 in order to control/dampen specific frequencies. This technique may be particularly helpful in scenarios where specific frequencies of noise from engine 150 are perceptible to passengers of aircraft 100 and known to cause discomfort to passengers of aircraft 100.

The structural design described above provides a further benefit when facesheet 210 and ceils 240 are both formed from thermoplastic. Since acoustic panels 200 can be composed of thermoplastic (e g., are entirely composed of thermoplastic), they may be heated and/or pressed in order to facilitate their shaping/contouring to any desired geometry within aircraft 100. This may be performed w hile preserving the integrity of facesheet 210, because facesheet 210 is capable of plastically deforming to conform to a desired surface geometry' of aircraft 100. Conforming acoustic panel 200 to a complex geometry’ may be performed without damaging acoustic panel 200 or otherwise decreasing its effectiveness. These properties of acoustic panel 200 also substantially increase the ease of installing acoustic panel 200.

Illustrative details of the fabrication and operation of acoustic panel 200 will be discussed with regard to FIGS. 16 and 17. Specifically, FIG. 16 describes fabrication of acoustic panel 200, while FIG. 17 describes operation of acoustic panel 200. Assume, that a thermoplastic sheet 500 has been received for forming into acoustic panel 200. FIG. 16 is a flow chart illustrating a method 1600 for fabricating an acoustic panel. The steps of method 1600 are described with reference to aircraft 100 and panel 200 of FIGS. 1-2, but those skilled in the art will appreciate that method 1600 may be performed in other systems. Tire steps of the flowcharts described herein are not all inclusive and may include other steps not shown. The steps described herein may also be performed in an alternative order.

According to FIG. 16, sheet 500 of thermoplastic is received and is subdivided into rows 620 (step 1602). Each row’ may comprise an equal portion of sheet 500, spanning across a. width (FIG. 5, W) of sheet 500. Sheet 500 is then conformed/stamped into rows 620, such that each row 620 comprises a three dimensional shape 650 (step 1604). For example, after stamping, adjacent rows 620 may be mirrored versions of the three dimensional shape. Next, sheet 500 is transformed/shaped into multi-celled core 206 by identifying fold lines (e.g., 630, 640) separating row s 620 (step 1606), and folding sheet 500 at the fold lines in a pleat fold (also known as an “accordion fold), which cause upper surfaces of adjacent rows to unit and also causes lower surfaces of adjacent row s to unite (step 1608). Specifically as show n in FIG . 6, for row 624, sheet 500 may be folded along fold lines (630, 640) with respect to adjacent rows (622, 626). This mates upper su rface 621 of row 622 against upper surface 623 of row 624, and further mates lower surface 625 of row 624 with lower surface 627 of row 626. The rows of the folded sheet 500 are also compressed together in the presence of heat, causing adjacent rows to fuse together into cells 240 (step 1610). This combines mated surfaces of sheet 500 together to integrate them into a unified, seamless single core 206.

After core 206 of cells 240 has been formed by folding-stamping rows 620 in the manner described above, backing sheet 220 is applied to core 206 (step 1612), as is facesheet 210 (step 1614). Facesheet 210 may then be fabricated to exhibit a desired POA, based on the cell size for core 206. For example, facesheet 210 may be punched with holes/slots in a predefined pattern correspond ing to the cells of core 206. Facesheet 210 includes openings that are aligned to direct a portion of airflow 155 across facesheet 210 into cells 240. resulting in acoustic control. Furthermore, facesheet 210 may be fused to core 206 to combine both of these elements into one integral piece of fused material. This completes acoustic panel 200. FIG. 17 is a flow chart illustrating a method 1700 for utilizing an acoustic panel 200. Assume, that acoustic panel 200 has been installed on aircraft 100 (e.g., at engine 150) for the purpose of damping/attenuating noise generated by inlet 152. As airflow 155 travels along inlet 152, facesheet 210 receives airflow 155 (step 1702). Facesheet 210 is integral with (i.e., combined/fused with to form a single integral w hole) and made from the same thermoplastic material as cells 240. Facesheet 210 directs soundwaves from airflow 155 into a cell 240 of acoustic panel 200, via openings 204 in facesheet 210 (e.g., perforations 1020, interstices 1140, and/or slots 1240) (step 1704). Cell 240 absorbs energy from the sound waves as the sound weaves travel through cell 240, such that audible frequencies (e.g., 20Hz to 20kHz) of sound generated by airflow 155 are attenuated (step 1706). Furthermore, airflow 155 is redirected off of backing sheet 220 of cell 240 (step 1708), and expelled outward from cell 240 via facesheet 210 (step 1710). These steps of directing, absorbing, reflecting, and expelling airflow for cells occurs as a continuous process (e.g., multiple times) as airflow' continues across cells 240.

Using methods 1600-1700, acoustic paneling may be fabricated quickly and efficiently, and may be utilized by an aircraft to increase passenger comfort. Furthermore, the acoustic panels discussed herein, because they are thermoplastic, are capable of being fabricated substantially planar, heated and/or pressed, and then shaped/formed to conform with complex geometries of the aircraft. This enhances both the ease of manufacturing panel 200, and the ease of installing panel 200.

Examples

In the following examples, additional processes, systems, and methods are described in the context of acoustic panels used for acoustic control (e.g., damping/attenuating, or enhancing, a sound). FIG. 18 is a block diagram of an engine 1800 utilizing an acoustic panel 1820. . As shown in FIG. 18, acoustic panel 1820 is located within inlet 1810. Panel 1820 includes backing sheet 1830, and core 1850, which has been folded and heated to form rows 1860 which define cells 1862. Each cell 1862 is surrounded by walls 1864, and includes a sound damping/attenuating septum 1866. Furthermore, each cell 1862 is covered by facesheet 1840, which include layers of thermoplastic 1842 and 1846, as well as a weave 1844 of linear elements 1845. Airflow I822 travels across face sheet 1840, and soundwaves from airflow 1822 are dampened/attenuated by cells 1862.

Referring more particularly to the drawings, the disclosure may be described in the context of an aircraft manufacturing and service method 1900 as shown in FIG. 19 and an aircraft 1902 as shown in FIG. 20. During pre-production, exemplar}' method 1900 may include specification and design 1904 of the aircraft 1902 and material procurement 1906. During production, component and subassembly manufacturing 1908 and system integration 1910 of the aircraft 1902 takes place. Thereafter, the aircraft 1902 may go through certification and delivery 1912 in order to be placed in sen ice 1914. While in service by a customer, the aircraft 1902 is scheduled for routine maintenance and sendee 1916 (which may also include modification, reconfiguration, refurbishment, and so on). Apparatus and methods embodied herein may be employed during any one or more suitable stages of the production and service method 1900 (e.g., specification and design 1904, material procurement 1906, component and subassembly manufacturing 1908, system integration 1910, certification and delivery 1912, sendee 1914, maintenance and service 1916) and/or any suitable component of aircraft 1902 (e.g., airframe 1918, systems 1920, interior 1922, propulsion 1924, electrical 1926, hydraulic 1928, environmental 1930).

Each of the processes of method 1900 may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer). For the purposes of this description, a system integrator may include without limitation any number of aircraft manufacturers and major-system subcontractors; a third party may include without limi tation any number of vendors, subcontractors, and suppliers; and an operator may be an airline, leasing company , military' entity, sendee organization, and so on.

As shown in FIG. 20, the aircraft 1902 produced by exemplary' method 1900 may include an airframe 1918 with a. plurality of systems 1920 and an interior 1922. Examples of high-level systems 1920 include one or more of a propulsion system 1924, an electrical system 1926, a hydraulic system 1928, and an environmental system 1930. Any number of other systems may be included. Although an aerospace example is shown, the principles of the invention may be applied to other industries, such as the automotive industry’.

As already mentioned above, apparatus and methods disclosed herein may be employed during any one or more of the stages of the production and sendee method 1900. For example, components or subassemblies corresponding to production stage 1908 may be fabricated or manufactured in a manner similar to components or subassemblies produced while the aircraft 1902 is in sendee. Also, one or more of the disclosed apparatus methods or a combination thereof may be utilized during the production stages 1908 and 1910, for example, by substantially expediting assembly of or reducing the cost of an aircraft 1902. Similarly, one or more of the disclosed apparatus methods or a combination thereof may be utilized while the aircraft 1902 is in sen ice, for example and without limitation, to maintenance and sendee 1916. For example, the techniques and systems described herein may be used for steps 1906, 1908, 1910, 1914, and/or 1916, and/or may be used for airframe 1918 and/or interior 1922. These techniques and systems may even be utilized for systems 1920, including for example propulsion 1924, electrical 1926, hydraulic 1928, and/or environmental 1930.

Panel 200 may comprise a portion of airframe 1918, and is manufactured during component and subassembly manufacturing 1908. Panel 200 may then be assembled into an aircraft in system integration 1910, and may for example be heated in order to facilitate its insertion and contouring into a portion of airframe 1918. Panel 200 may then be utilized in sendee 1914 to reduce noise until w ear renders panel 200 unusable. Then, in maintenance and service 1916, panel 200 may be discarded and replaced with a newly manufactured panel.

Any of the various control elements (e.g., electrical or electronic components) shown in the figures or described herein may be implemented as hardware, a processor implementing software, a processor implementing firmware, or some combination of these. For example, an element may be implemented as dedicated hardware. Dedicated hardware elements may be referred to as “processors”, “controllers”, or some similar terminology. When provided by a processor, the functions may be provided by a single dedicated processor, by a single shared processor, or by a plurality of individual processors, some of which may be shared. Moreover, explicit use of the term "‘processor” or “controller” should not be construed to refer exclusively to hardware capable of executing software, and may implicitly include, without limitation, digital signal processor (DSP) hardware, a network processor, application specific integrated circuit (ASIC) or other circuitry, field programmable gate array (FPGA), read only memory (ROM) for storing software, random access memoiy (RAM), non-volatile storage, logic, or some other physical hardw are component or module.

Also, an element may be implemented as instructions executable by a processor or a computer to perform the functions of the element. Some examples of instructions are software, program code, and firmware. The instructions are operational when executed by the processor to direct the processor to perform the functions of the element. The instructions may be stored on storage devices that are readable by the processor. Some examples of the storage devices are digital or solid-state memories, magnetic storage media such as a magnetic disks and magnetic tapes, hard drives, or optically readable digital data storage media.

Further details of the features of acoustic panel 200' are described with regard to FIGS. 21-22. Specifically, FIGS. 21-22 illustrate a fully fabricated acoustic panel 200’. FIG. 21 is an underside view of panel 200’ that illustrates a view of a face 202’ of panel 200’ indicated by view’ arrow s 21 of FIG. 2. As shown in FIG. 21 face 202’ of acoustic panel 200' includes openings 204’ through which airflow may enter and/or exit panel 200’ for acoustic control. The face 202’ of acoustic panel 200’ may include a facesheet having openings 204' which are designed to provide low drag. FIG. 22 illustrates a section cut view’ of a side of acoustic panel 200’ illustrated by view’ arrow’s 22 of FIG. 21. FIG. 22 illustrates that panel 200’ includes a core 206’ which includes cells 240’ defined by borders/walls 230’. Each cell 240’ in panel 200’ is sandwiched between (i.e., encapsulated by) a facesheet 210’ and a backing sheet 220’, and i this embodiment each cell 240’ may include a septum 400’ that absorbs and controls, acoustic energy. Facesheet 210’ is exposed to airflow 155 across panel 200’. Furthermore, as shown in FIG. 22, openings 204' allow sound waves/vibrations from airflow 155 to enter cells 240’. These sound waves from airflow’ 155 may then be attenuated by travel within cells 240’ and/or reflection off of backing sheet 220’.

Further discussion of acoustic panel 200’ will be made with regard to FIG. 23, w hich illustrates a system that actively fabricates a facesheet. The fabrication techniques discussed herein beneficially forego traditional techniques of manually creating each cell of an acoustic panel, and utilize thermoplastic (e.g., Polyether ether ketone (PEEK) or Polyether ketone ketone (PEKK) or similar) materials in order to ensure that various different layers, liners, etc. may be bonded together via heat without a need for supplementary adhesives. Hence, an acoustic panel may be fabricated in its entirety via automated AFP layup and/or 3D printing techniques. FIG. 23 is a diagram illustrating an automated system 500’ for fabricating acoustic paneling. . Sy stem 500’can include AFP machine 520’, which includes a kinematic chain 522’ of rigid bodies 521' and actuators 523’ that reposition end effector 524' over a core 550' of acoustic cells 240’. End effector 524’ includes dispenser 528’, which dispenses thermoplastic CFRP and/or thermoplastic. Other 3D printable materials may also be used, such as-metals for metal structures. Dispenser 528' may comprise a dispenser which lays up tows of thermoplastic CFRP atop core 550’. Dispenser 528’ may comprise a 3D printing device. As used herein, “thermoplastic CFRP” is a carbon fiber reinforced thermoplastic. The carbon fiber described herein may be long fiber CFRP in which multiple strands of carbon fiber are aligned parallel with each other and extend for long distances (e.g.., centimeters or meters). The carbon fiber may comprise short “chopped fiber” having a random orientation.

End effector 524’ further includes laser 526’, which emits beam 527’ of laser energy 599’ (e.g., infrared (IR) heat energy). This laser energy 599’ is utilized to fuse different layers of thermoplastic together. Laser 526’ can follow dispenser 528’ as AFP machine 520’ continues in a direction of travel 598’.Hence, laser 526’ is capable of directly radiating laser energy 599’ onto locations (L) that have just been laid-up or printed in order to heat thermoplastic material 597’ to a fusing temperature (e.g., a melting temperature). This facilitates rapid fusing in order to form an acoustic panel 200'. FIG. 23 further illustrates controller 510’ and memory 512’. Memory 512’ stores Numerical Control (NC) program 514'. NC program 514' includes instructions that direct elements of kinematic chain 522’ and end effector 524' in laying up portions of facesheet 530’. NC program 514’ can further include instructions for operating laser 526'. These instructions may indicate when and where to activate laser 526’, an amount of energy to radiate at each location where laser 526’ is activated (e.g., to ensure sufficient heat transfer), etc.

As shown in FIG. 23, facesheet 530’ comprises multiple components. Base layer 536’ comprises thermoplastic CFRP directly laid-atop core 550’. A surface 538' of core 550’ is also visible. Base layer 536’ may comprise multiple tows which have been laid-up in a pattern over core 550’ of cells 240’. Base layer 536' can be 3D printed to form the pattern. In either case, the pattern follows wails 230' of ceils 240’, and leaves a gap/opening (shown as opening/gap 600' of FIG. 24) over each cell 240’. The opening enables acoustic energy to travel into and out of cell 240’. The next component is liner 534’. which comprises porous thermoplastic. Porous thermoplastic liner 534’ covers the openings over each cell 240’ defined by base layer 536’. The porous nature of liner 534' enables acoustic energy to enter cell 240’ for attenuation.

The final component laid-up by AFP machine 520’ is cap layer 532', which comprises thermoplastic CFRP. Like base layer 536’, cap layer 532' is laid-up in a pattern that leaves gaps/openings. This pattern may include openings which are shaped and arranged in order to provide low drag over acoustic cells 240’ (i.e., a smooth(er) aerodynamic surface). The carbon fiber in cap layer 532' provides mechanical support to liner 534' without altering the fundamental acoustic properties of facesheet 530'. The patterns described herein may follow the contours of walls 230' at core 550', and are illustrated with regard to FIG. 24 below. FIG. 24 is atop view of facesheet 530' indicated by arrows 6 of FIG. 23Cap layer 532’ and liner 534’ are visible., and cap layer 532’ has been laid-up to form pattern 620. Walls 230’ are located deep underneath cap layer 532’, and liner 534’ is visible at gaps/openings 600'. Gaps 600' are aligned with gaps/openings defined by base layer 536', and hence liner 534’, which is permeable, is the only barrier between external acoustic energy and the internal portions of each cell 240’. Only locations where cap layer 532’ has been dispensed are heated by laser 526’ (as indicated by Δ on FIG. 24). Acoustic energy 620 travels into a ceil 240’ via an opening 600' and exits the opening 600' as attenuated acoustic energy 622’.

With the physical features of facesheet 530’ described above, a method describing illustrative details of the operation of system 500’ of FIG. 23 will be discussed with regard to FIG. 25. Assume, that a user has generated an NC program 514' which includes instructions for fabricating acoustic paneling from core 550’ of cells 240’. FIG. 25 is atop view of further acoustic paneling arranged in pattern 700'. Pattern 700’ may comprise overlapping tows 714’ which define openings 710’ over corresponding diamondshaped cells. The cells are bordered by CFRP 712’. As shown in FIG. 25, openings 710’ are arranged with respect to airflow 155 such that the width (W, the dimension parallel to airflow' 155) of each opening 710’ is substantially smaller than the height (H, the dimension perpendicular to airflow 155) of each opening 710’. This helps to provide low drag. That is, by directing airflow 155 across the shorter dimension (i.e., width) of each opening 710’, drag is reduced. Dispensing of the cap layer 532’ can formthe gaps/openings such that a width of each gap/opening parallel to expected airflow is less than a height of each gap perpend icular to expected airflow.

An acoustic panel 200’ having pattern 700’ may therefore include a core 550’ comprising multiple cells 240’ of thermoplastic having walls that are fused together, and a facesheet 530’ fused to a surface 538’ of core 550’. The facesheet 530’ includes multiple openings 600’ through which sound waves enter the cells, and a porous liner 534' within the openings provides acoustic control by keeping a majority of airflow across the openings connected and laminar, thereby reducing drag. Liner 534’ is fused with the rest of facesheet 530’, but remains porous.

Using the acoustic paneling described above, a method may be used for performing acoustic control of jet engine noise via an acoustic panel. This is illustrated w'ith regard to method 800' of FIG. 26A. The method may include, for example, receiving airflow' across openings of a facesheet 530’ of the panel 200’ that is fused to a multi-celled core 550’ of the panel 200’ while keeping a majority' of the airflow laminar (step 802 ). This includes maintaining laminar airflow across the openings by placing a porous liner in the openings that resists airflow into the cells (step 804’). That is, liner 534’ provides some resistance to airflow entering the cell through the opening resulting in maintaining laminar flow across the openings. Thus, a majority of the airflow remains connected to itself (i,e., not disconnected, fragmentary, or turbulent) and laminar, thereby reducing drag and improving airplane performance, fuel bum etc. The method may also include directing the airflow into cells 240’ of the acoustic panel 200’ via the openings in the facesheet through a porous liner 534' (step 806’), and absorbing energy from the airflow as the airflow travels within the cells 240’ such that audible frequencies of sound generated by the airflow are attenuated by the cells 240’ (step 808"). The method may also include reflecting the airflow off of a backing sheet 220’ for the cells 240' (step 810’), and expelling the airflow from the cells 240’ via the facesheet 530’ (step 812'). FIG. 26B is a flowchart illustrating a method 850’ for fabricating acoustic paneling. . The steps of method 850’ are described with reference to system 500’ of FIG. 23. but those skilled in the art will appreciate that method 850’ may be performed in other systems. The steps of the flowcharts described herein are not all inclusive and may include other steps not shown. Hie steps described herein may also be performed in an alternative order.

In step 852’, system 500’ acquires core 550’ of acoustic cells 240’. Core 550’ may comprise a linear sheet of cells arranged in any suitable pattern (e.g., a tessellating pattern of hexagonal cells, triangular cells, square cells, etc.). Core 550’ can be “open'’ in that it has neither a backing sheet nor a facesheet. Core 550’ may therefore be made as a. single extruded piece of thermoplastic, or may be 3D printed thermoplastic. Core 550’ may be acquired by either placing core 550’ in a desired location with respect to system 500’, or by actively printing core 550’ via system 500’. With core 550’ acquired, a septum 400’ may be inserted into each cell 240’, or may even be 3D printed into each cell via dispenser 528’.

Where dispenser 528’ is a 3D printing device, dispenser 528’ may 3D print individual tows (comprising thermoplastic and carbon fiber) via a separate nozzle than for components which comprise only thermoplastic. When printing thermoplastic materials that are porous in nature (e.g., where a specific level of porosity is desired in order to provide acoustic performance (enabl ing acoustic energy to freely enter cells 240’) while also ensuring smooth properties that enhance aerodynamics), a temperature of the dispensing nozzle, an amount of material ejected, an amount of ejection pressure, and/or a cooling time may be adjusted in order to fine tune the porosity to desired characteristics.

With cells 240’ ready for creation of a facesheet, system 500’ initiates fabrication of a. facesheet 530’ covering core 550’ of acoustic cells 240’ (step 854’). The facesheet includes three separate components. The first component is base layer 536’, which is dispensed atop acoustic cells 240’ by dispenser 528’, and leaves openings 600’ over cells 24 which allow acoustic energy to freely enter ceils 240' (step 856’). After base layer 536’ has been applied by dispenser 528’, laser 526’ may fused base layer 536’ to core 550’ by radiating beam 527' of laser energy directly onto locations at which layer 536' has been dispensed. This heats thermoplastic polymer within base layer 536’. causing fusing (e.g.., via melting) between base layer 536’ and core 550’.

Next, cells 240’ are covered by liner 534’, which is applied atop base layer 536’ (step 858"). Liner 534’ can be applied as a continuous layer that covers gaps 600’ as well as base layer 536’. Liner 534’ can be a prefabricated sheet of therm oplastic having a known porosity (e.g., a percent open area of twenty to eighty percent). Liner 534’can be printed via dispenser 528’. Liner 534’ attenuates acoustic energy while still enabling acoustic energy to flow into cells 240’ for further attenuation. However, since liner 534' is porous, it may be desirable to enhance the structural strength of facesheet 530’ (e.g.. in order to ensure that materials impacting facesheet 530’ do not remove substantial amounts of material from facesheet 530’.

In order to ensure that desired levels of structural strength are achieved for facesheet 530’, controller 510’ directs dispenser 528’ to dispense cap layer 532’ atop liner (step 860’). Cap layer 532' is laid up in the same pattern as base layer 536'. Because cap layer 532’ includes carbon fiber, cap layer 532’ is substantially stronger than liner 534’.

With the components of facesheet 530’ fully in place, controller 510’ operates laser 526' to radiate laser energy (e.g., IRheat) onto locations where cap layer 532’ intersects liner 534’ (step 862’). That is, heat applied via beam 527’ of laser energy from laser 526’ is sufficient to cause cap layer 532’ to fuse with underlying components of facesheet 530’ (e.g., liner 534’ and base layer 536"). Controller 510’ may perform this step substantially concurrently with the dispensing of layer 532’, such that tows of CFRP are fused via laser 526’ immediately after they are laid up. Alternatively, controller 510’ may cause laser 526’ to perform fusing via an entirely separate run from the run in which thermoplastic CFRP is dispensed. Tn either case, laser 526’ is operated in such a manner that no laser energy is directly radiated onto liner 534’ in gaps 600’, as this could cause liner 534’ to melt and become non-porous in such gaps. Thus, laser 526’ selectively applies heat only to locations at which cap layer 532’ overlaps liner 534'. As an additional step, a continuous backing sheet may be applied (e.g., via 3D printing or AFP tow layup) in order to complete the fabrication of cells 240’.

Method 850' provides an advantage over prior techniques in that it allows for rapid fabrication of large sets of acoustic cells. Furthermore, where 3D printing techniques are utilized, large sets of acoustic cells may be fabricated to fit complex 3D contours, such as those found along the interior of an engine cowling.

Examples

In the following examples, additional processes, systems, and methods are described in the context of acoustic paneling for aircraft. FIG. 27 is a. block diagram of an engine 900' util izing an acoustic panel 920’. Engine 900’ is a component of an aircraft that provides thrust to lift the aircraft during flight. As shown in FIG. 27, acoustic panel 920’ is located within inlet 910’. Panel 920’ attenuates acoustic energy generated by the airflow 922’ through engine 900’. Panel 920’ includes backing sheet 930’, and core 950’ includes cells 962’. Each cell 962’ performs attenuation of acoustic energy, and backing sheet 930’ provides a backing for each cell 962'. Each cell 962’ is surrounded by walls 964’, and may include septum 966’ for attenuating acoustic energy entering and/or exiting the cell. Gap 968’ between pattern 967’ for facesheet 940’ are also shown. These gaps enable acoustic energy to enter and/or exit cells 962’. Furthermore, cells 962’ are covered by facesheet 940’, which includes cap layer 942’ and base layer 946’ of thermoplastic CFRP. as well as porou s thermoplastic l iner 944'. Facesheet 940’ facilitates attenuation of acoustic energy by further attenuating acoustic energy which has entered a cell 962’. Cap layer 942’ and base layer 946' include tow 947’. Aiiflow 922’ travels across facesheet 940’ and sound waves from airflow 922’ are dampened/attenuated by cells 962’. FIG. 28 depicts AFP machine 1070’. AFP machine 1070’ may be utilized prior to insertion of acoustic panel 1020’ into engine 900’ in order to fabricate acoustic panel. Thus, AFP machine 1070’ is located in a manufacturing and assembly environment, while engine 900’ is utilized after manufacturing and assembly is complete and an aircraft is actively operating. , AFP machine 1070’ can include controller 1072’ as w;ell as memory 1074’. Controller 1072’ may comprise any suitable component for controlling the operations of an end effector, and may comprise for example a hardware processor or custom circuitry. Memory' 1074’ comprises any suitable device capable of storing data for reading by a computer system, and stores Numerical Control (NC) program 1075’ having instructions for operating end effector 1090’. The instructions may for example indicate how and where to move end effector 1090’, as well as indicating when to activate dispenser 1092’ and/or laser 1094’. Kinematic chain 1080’ includes actuator 1084’ and rigid body 1082’ which operate in tandem to facilitate repositioning and/or reorienting end effector 1090’ based on instructions in NC program 1075’. Here,, end effector 1090’ can includeboth dispenser 1092' and laser 1094’. Dispenser 1092’ dispenses tows of material in order to form facesheet 940’ of FIG. 28, and laser 1094’ fuses cap layer 942’, base layer 946’, and/or liner 944’ of FIG. 28 in order to adhere facesheet 940’ to cells 962' of core 950’ (as shown in FIG. 28).

Any of the various control elements (e.g.. electrical or electronic components) shown in the figures or described herein may be implemented as hardware, a processor implementing software, a processor implementing firmware, or some combination of these. For example, an element may be implemented as dedicated hardware. Dedicated hardware elements may be referred to as “processors”, “controllers’', or some similar terminology. When provided by a processor, the functions may be provided by a single dedicated processor, by a single shared processor, or by a plurality of individual processors, some of which may be shared. Moreover, explicit use of the term “processor” or ‘controller” should not be construed to refer exclusively to hardw are capable of executing software, and may implicitly include, without limitation, d igital signal processor (DSP) hardware, a network processor, application specific integrated circuit (ASIC) or other circuitry, field programmable gate array (FPGA), read only memory (ROM) for storing software, random access memory (RAM), non-volatile storage, logic, or some other physical hardw are component or module.

Also, a control element may be implemented as instructions executable by a processor or a computer to perform the functions of the element. Some examples of instructions are software, program code, and firmware. The instructions are operational when executed by the processor to direct the processor to perform the functions of the element. The instructions may be stored on storage devices that are readable by the processor. Some examples of the storage devices are digital or solid-state memories, magnetic storage media such as a magnetic disks and magnetic tapes, hard drives, or optically readable digital data storage media.

The present invention is also referred to in the following clauses which are not to be confused with the claims. A1. A method comprising: performing acoustic control of jet engine noise via an acoustic panel, comprising: receiving airflow across openings of a facesheet of the panel that is fused to a multi-celled co re of the panel ; directing the airflow’ into cells of the acoustic panel via the openings in the facesheet; absorbing energy from the airflow as the airflow' travels within the cells such that audible frequencies of sound generated by the ai rflow are attenuated by the cells : reflecting the airflow off of a backing sheet for the cells : and expelling the airflow from the cells via the facesheet. A2. There is also provided, the method of paragraph Al further comprising: directing the airflow’ through a septum of the cell prior to the airflow reflecting off of the backing sheet of the cell. A3. There is also provided, the method of paragraph Al or A2 wherein: directing the airflow comprises receiving the airflow via a slot of the facesheet that is elongated in an expected direction of airfl ow across the facesheet, A4. There is also provided, the method of any of paragraphs A1-A3 further comprising: directing, absorbing, reflecting, and expelling the airflow multiple times as the airflow continues across multiple cells of the acoustic panel.

According to a further aspect of the present invention, there is provided:

Bl. A method comprising: receiving a sheet of thermoplastic paper ; conforming the sheet into rows that each comprise a three dimensional shape; transforming the sheet into a multi-celled core by: identifying fold lines separating the rows ; folding the sheet at the fold lines in a pleat fold, thereby uniting upper surfaces of adjacent rows and uniting lower surfaces of adjacen t rows ; and compressing the rows of the folded sheet together in the presence of heat, causing adjacent rows to fuse together into cells ; optionally applying a backing sheet to the core ; and applying a facesheet to a surface of the core that includes openings which direct a portion of airflow across the facesheet into the cells, resulting in an acoustic panel that performs acoustic control . B2. There is also provided, the method of paragraph Bl wherein: the facesheet comprises a thermoplastic material; and applying the facesheet comprises fusing the facesheet to the surface via the application of heat and pressure. B3. There is also provided, the method of paragraph Blor B2 wherein: the facesheet includes multiple slots that are each elongated in an expected direction of airflow across the facesheet: and the method further comprises aligning the slots of the facesheet such that airfl ow may enter each cell of the acoustic panel via at least one of the slots. B4. There is also provided, the method of any of the paragraphs Bl to B3 farther comprising: installing the acoustic panel into a jet engine inlet such that flow through the inlet contacts the face sheet . B5. There is also provided, the method of any of the paragraphs B1-B4 further comprising: perforating the facesheet at each of the cells. B6. There is also provided, the method of any of the paragraphs B1-B5 further comprising: laying up the facesheet as an open weave of tows, wherein the open weave includes at least one interstice per cell. B7. There is also provided, the method of any of the preceding paragraphs B1-B6 further comprising: selecting audible frequencies of sound to attenuate via the acoustic panel; and selecting a Percentage Open Area (POA) for the open weave that attenuates the selected frequencies of sound. B8. There is also provided, the method of any of the preceding paragraphs B1-B7 further comprising: forming the facesheet as a layer of thermoplastic in contact with the surface, a layer of open weave in contact with the layer of thermoplastic, and an additional layer of thermoplastic in contact with the open weave, or further comprising: forming the facesheet as a layer of open weave in contact with the surface, and an additional layer of thermoplastic in contact with the open weave. B9. There is also provided, the method of any of the preceding paragraphs B1-B8 further comprising: inserting a septum into each of the cells. BIO. There is also provided, the method of any of the preceding paragraphs B1-B9 further comprising: applying heat and pressure to the acoustic panel to facilitate plastic deformation of the acoustic panel; and conforming the acoustic panel to a contour while the acoustic panel is heated.

According to a further aspect of the present invention, there is also provided:

Cl. An apparatus comprising: an acoustic panel comprising: a core comprising multiple cells of thermoplastic having walls that are fused together; and a face sheet fused to a surface of the core, the facesheet including multiple openings through which sound waves enter the cells, resulting in acoustic control. C2. There is also provided, the apparatus of paragraph Cl wherein: the core comprises a single sheet of Poly Ether Ether Ketone (PEEK) thermoplastic paper. C3. There is also provided, the apparatus of paragraph Cl or C2 wherein: the facesheet comprises a single sheet of Poly Ether Ether Ketone (PEEK) thermoplastic paper that has been fused with the core. C4. There is also provided, the apparatus of any of the paragraphs C1-C3 wherein: the facesheet includes multiple slots that are each elongated in an expected direction of airfl ow across the facesheet and the slots of the facesheet are aligned such that airfl ow may enter each cell of the acoustic panel via at least one of the slots. C5. There is also provided, the apparatus of any of the paragraphs Cl to C4 wherein: the acoustic panel is installed into a jet engine inlet and is oriented such that flow through the inlet contacts the facesheet. C6. There is also provided, the apparatus of any of the paragraphs C1-C5 wherein: the facesheet comprises an open weave of linear elements, wherein the open weave that includes an interstice at each of the cells, preferably wherein: the open weave exhibits a Percentage Open Area (POA), calculated by comparing area filled by openings to a total area of the face sheet, that corresponds with attenuation of an audible frequency of sound. C7. There is also provided, the apparatus of any of the paragraphs Cl- C6 wherein: the facesheet comprises a layer of thermoplastic in contact with the surface, a layer of open weave in contact with the layer of thermoplastic, and an additional layer of thermoplastic in contact with the open weave, or wherein: the facesheet comprises a. layer of open weave in contact with the surface, and an additional layer of thermoplastic in contact with the open weave. C8. There is also provided, the apparatus of any of the paragraphs C1-C7 further comprising: an acoustically controlling septa (1320’) inserted into each of the cells. DI. A method comprising: acquiring a core of acoustic cells ; and fabricating a facesheet covering the core by: dispensing a base layer of material atop the acoustic cells w hile leaving openings into each of the acoustic ceils ; covering the openings by applying a liner of material atop the base layer; dispensing a cap layer atop the liner while leaving gaps in the cap layer over the acoustic cells ; and fusing the cap layer to the liner by directly radiating laser energy onto locations where the cap layer has been dispensed . D2. There is also provided, the method of paragraph DI wherein: dispensing the cap layer forms the gaps such that a width of each gap parallel to expected airflow' is less than a height of each gap perpendicular to expected airflow'. D3. There is also provided, the method of paragraph DI or D2 wherein: fusing the cap layer to the liner further comprises fusing the liner to the base layer. D4. There is also provided, the method of any of the paragraphs D1-D3 wherein: the core of acoustic ceils is thermoplastic: and the method further comprises fusing the base layer to the core of acoustic cells by directly radiating laser energy onto locations where the base layer has been dispensed. D5. There is also provided, the method of any of the paragraphs D1-D4 further comprising: printing the base layer via three dimensional (3D) printing techniques. D6. There is also provided, the method of any of the paragraphs D1-D5 further comprising: printing the liner via three dimensional (3D) printing techniques. D7. There is also provided, the method of any of the paragraphs D1-D6 wherein: fusing the cap layer comprises directly radiating laser energy only onto locations at which the cap layer overlaps the liner. D8. There is also provided, the method of any of the paragraphs D1-D7 wherein: fusing the cap layer causes the liner to become non-poroiis at locations where laser energy is directly applied. D9. There is also provided, the method of any of the paragraphs D1-D8 wherein: material for the base layer and the cap layer comprises Carbon Fiber Reinforced Polymer (CFRP) thermoplastic; and material for the liner comprises thermoplastic.

El. A non-transitory computer readable medium embodying programmed instructions which, when executed by a processor, are operable for performing a method comprising: acquiring a core of acoustic cells ; and fabricating a facesheet covering the core by: dispensing a base layer of material atop the acoustic cells while leaving openings into each of the acoustic ceils ; covering the openings by applying a liner of material atop the base layer dispensing a cap layer atop the liner while leaving gaps in the cap layer over the acoustic cells ; and fusing the cap layer to the liner by directly radiating laser energy onto locations where the cap layer has been dispensed . E2. There is also provided, the medium of paragraph El wherein: fusing the cap layer to the liner further comprises fusing the liner to the base layer. E3. There is also provided, the medium of paragraphs El or E2 wherein: the core of acoustic cells is thermoplastic; and the method further comprises fusing the base layer to the core of acoustic cells by directly radiating laser energy onto locations where the base layer has been dispensed. E4. There is also provided., the medium of any of the paragraphs E1-E3 wherein the method further comprises: printing the base layer via three dimensional (3D) printing techniques. E5. There is also provided, the medium of any of the paragraphs E1-E4 wherein the method further comprises: printing the liner via three dimensional (3D) printing techniques. E6. There is also provided, the medium of any of the paragraphs E1-E5 wherein: fusing the cap layer comprises directly radiating laser energy only onto locations at which the cap layer overlaps the liner. E7. There is also provided, the medium of any of the paragraphs E1-E6 wherein: fusing the cap layer causes the liner to become non-porous at locations where laser energy is directly applied. E8. There is also provided, the medium of any of the paragraphs E1-E7 wherein: material for the base layer and the cap layer comprises Carbon Fiber Reinforced Polymer (CFRP) thermoplastic: and material for the liner comprises thermoplastic.

Fl. A system comprising: an Automated Fiber Placement (AFP) machine , comprising: a kinematic chain of actuators and rigid bodies ; an end effector comprising: a dispenser that dispenses material; and a laser that radiates laser energy which fuses the material; and a controller that operates the end effector to operate in accordance with instructions in a Numerical Control (NC) program that directs the AFP machine to: acquire a core of acoustic cells, and fabricate a facesheet covering the core by: dispensing a base layer of material atop the acoustic cells while leaving openings into each of the acoustic cells, covering the openings by applying a liner of porous material atop the base layer, dispense a cap layer of material atop the liner while leaving gaps in the liner over the acoustic cells, and fuse the cap layer to the liner by directly radiating laser energy onto locations where the cap layer has been dispensed. F2. There is also provided, the system of paragraph Fl wherein: the laser fuses the cap layer to the liner while fusing the liner to the base layer. F3. There is also provided, the system of paragraph Fl or F2 wherein: the core of acoustic cells is thermoplastic; and the laser fuses the base layer to the core of acoustic cells by directly radiating laser energy onto locations where the base layer has been dispensed. F4. There is also provided, the system of any of the paragraphs F1-F3 wherein: the dispenser prints the base layer via three dimensional (3D) printing techniques. F5. There is also provided, the system of any of the paragraphs F1-F4 further comprising: the dispenser prints the liner via three dimensional (3D) printing techniques. F6. There is also provided, the system of any of the paragraphs F1-F5 wherein: the laser Rises the cap layer by directly radiating laser energy only onto locations at which the cap layer overlaps the liner. F7. There is also provided, the system of any of the paragraphs F1-F6 wherein: material for the base layer and the cap layer comprises Carbon Fiber Reinforced Polymer (CFRP) thermoplastic; and material for the liner comprises thermoplastic.

Gl. A method comprising: performing acoustic control of jet engine noise via an acoustic panel, comprising: receiving airflow across openings of a facesheet of the panel; maintaining laminar airflow across the openings ; di recting the airflow into cells of the acoustic panel via the openings in the facesheet through a porous liner and absorbing energy from the airflow as the airflow travels within the cells . G2. There is also provided, the method of paragraph Gl wherein: each of the openings is arranged with respect to airflow such that a dimension of the opening parallel to ai rflow is smalle r than a dimension of the opening pe rpend icular to airflow. G3. There is also provided, the method of paragraph G1 or G2 wherein: the porous liner is fused to the facesheet. G4. There is also provided, the method of any of the paragraphs G1-G3 wherein: the facesheet is fused to a multi-celled core of the panel. G5. There is also provided, the method of any of the paragraphs GI-G4 further comprising: placing a porous liner in the openings that resists airflow' into the cells such that audible frequencies of sound generated by the airflow are attenuated by the cells; reflecting the airflow off of a backing sheet for the cells; and expelling the airflow from the cells via the facesheet.

Hl. An apparatus comprising: an acoustic panel comprising: a core comprising multiple cells having walls that are fused together; and a facesheet including multiple openings through which sound w aves enter the cells, and a porous liner in the openings. H2. There is also provided, the apparatus of paragraph Hl wherein: each of the openings is arranged with respect to airflow such that a dimension of the opening parallel to airflow is smaller than a dimension of the opening perpendicular to airflow. H3. There is also provided, the apparatus of paragraph Hl or H2 wherein: the porous liner is fused to the facesheet. H4. There is also provided, the apparatus of any of the paragraphs Hl to H3 wherein: the cells are thermoplastic. H5. There is also provided, the apparatus of any of the paragraphs Hl -H4 wherein: the facesheet is fused to a surface of the core. H6. There is also provided, the apparatus of any of the paragraphs H1-H5 wherein: the liner resists airflow into the cells, providing acoustic control by maintaining laminar airflow across the openings, thereby reducing drag. KI. A method comprising: performing acoustic control of jet engine noise via an acoustic panel, comprising: receiving ai rflow across openings of a facesheet of the panel; arranging each of the openings with respect to airflow such that a dimension of the opening parallel to airflow (W) is smaller than a dimension of the opening perpendicular to airflow (H). di recting the airflow into cells of the acoustic panel via the openings in the facesheet through a porous liner ; and absorbing energy from the airflow as the airflow travels within the ceils .

The scope of the disclosure is defined by the following claims and any equivalents thereof.

Claims

An apparatus for attenuating jet engine noise in an aircraft, the apparatus comprising: an acoustic panel with a core, which core comprises several cells, and a front film arranged on a first surface of the core, which front film comprises several openings through which sound waves enter the cells, resulting in acoustic control.

The device of claim 1, further comprising a rear film arranged on a second surface of the core, opposite the first surface lacquer of the core on which the front film is arranged.

Device as claimed in claim 1 or 2, wherein the core is made of thermoplastic material and the walls of the cells are attached to each other.

Device as claimed in claim 1, 2 or 3, wherein the front film and / or the rear film are made of thermoplastic material, and wherein the front film and / or the rear film are attached to each other on the first and / or the second surface of the core.

The device of any preceding claim, further comprising a porous liner in the front film openings, which porous liner is preferably attached to the front film.

The device of any one of the preceding claims, further comprising an acoustically controlling septum arranged in one or more of the cells.

The device of any preceding claim, wherein the front film openings are elongated slots in a night direction of the air flow over the front film, which slots are aligned such that the air flow passes each cell of the acoustic panel through at least one of the slots can enter.

Device according to any of the preceding claims, wherein each of the openings is arranged relative to the air flow such that a dimension of the opening parallel to the air flow is smaller than a dimension of the opening perpendicular to the air flow.

The device of any preceding claim, wherein the front film comprises an open tissue of linear elements, wherein the open tissue has an interstitium at each of the cells, wherein the open tissue preferably has a Percentage Open Area, POA), calculated by comparing the aperture-filled surface with an overall surface of the front film, corresponding to attenuation of an audible sound sequence.

Device as claimed in any of the foregoing claims, wherein a layer of open fabric is arranged between the front foil and the inner roof of the core.

The device of claim 10, wherein a thermoplastic layer is sandwiched between the layer of open fabric and the surface of the core.

The device of any preceding claim, wherein the core comprises a single polyetheretherketone (PEEK) thermoplastic paper film, and / or wherein the front film comprises a polyetheretherketone (PEEK) thermoplastic paper single film attached to the core, includes,

A jet engine comprising a device according to any of the preceding claims 1-12, wherein the device is preferably installed in an inlet of the jet engine and wherein the device is oriented such that the flow through the inlet makes contact with the front foil of the device.

A method for performing acoustic control of jet engine noise, using an apparatus according to any one of the preceding claims, the method comprising the steps of: receiving air streams through the openings of the front film arranged on the multi-cellular core of the acoustic panel of the device, whereby the air flow is directed through the front film openings to the cells, which openings are preferably elongated in a night direction of the air flow over the front film; absorbing energy from the airflow as the airflow moves within the cells so that audible frequencies of sound generated by the airflow are attenuated by the cells.

The method of claim 14, wherein the air flow is reflected from the posterior cell core film and discharged from the cell core via the anterior film.

The method of any one of claims 14 or 15, wherein the air flow is directed through the septum of each cell before the air flow reflects from the posterior film.

The method of any one of the preceding claims 14-16, further comprising directing, absorbing, reflecting, and outputting the airflow as the airflow passes through several cells of the acoustic panel.

A method according to any one of the preceding claims 14-17, wherein when the acoustic panel is provided with a porous liner, the liner provides an acoustic control by maintaining a laminated flow over the openings thereby reducing the resistance.

A method of producing a device according to any of the preceding claims 1-12, comprising the steps of: arranging a thermoplastic paper film in rows, each row comprising a three-dimensional shape, identifying folding lines separating the rows . folding the film on the identified fold lines in a fold fold, whereby the upper surfaces of adjacent rows are joined and lower surfaces of neighboring runs are joined in the film, compressing the rows of the film. folded foil in the presence of heat, whereby adjacent rows are attached to each other into cells, thus forming a cell core, and applying a front foil to a first surface of the core, which front foil has openings corresponding to the formed cells.

The method of claim 19. wherein a rear film is arranged on a second surface of the core opposite the first surface of the core.

The method of any one of claims 19 or 20, comprising the further steps of introducing the septum into each cell.

The method of any one of claims 19 to 21, wherein the front film is attached to the first surface of the core by heat and pressure.

The method according to any of claims 19-22. wherein the posterior film is attached to the second surface of the core by heat and pressure.

The method of any one of claims 19-23, further comprising the step of perforating the front film at each of the cells.

Method according to any of the preceding claims 19-24, further comprising applying heat and pressure to the device in order to facilitate plastic deformation thereof and thereby make the device correspond to a desired contour.

The method of any one of the preceding claims 19-25, wherein the front film is applied by laying on as an open fabric of linear strands, wherein the open fabric comprises at least one miter stage per cell.

The method of claim 26, further comprising selecting audible audio frequencies to attenuate through the acoustic panel: and selecting a Percentage Open Area (POA) of the open tissue that attenuates the selected audio frequencies.

The method of any one of claims 19-27, further comprising forming the front film as a first thermoplastic layer in contact with the first surface of the core, and a layer of open fabric in contact with this thermoplastic layer and an additional thermoplastic layer that is in contact with the open fabric.

The method of any one of claims 19-27, further comprising: forming the front film as a layer of open fabric in contact with the first surface of the core and an additional thermoplastic layer in contact with the open fabric.

The method of any one of claims 19 to 29, further comprising the step of arranging a porous liner in the front film openings.

A method of producing an apparatus according to any one of the preceding claims 1-12, comprising the steps of: obtaining a core of acoustic cells; and the. manufacture a front foil that covers the core by dispensing. a base layer of material on top of the acoustic cells while openings are left in each of the acoustic cells; covering the openings by applying a liner of material on top of the base layer: delivering a cover layer on top of the liner while leaving gaps in the cover layer over the acoustic cells: and attaching the cover layer to the liner by direct blasting of laser energy at the locations where the cover layer has been delivered.

The method of claim 31. further comprising fusing the base layer to the core of the acoustic cells by directly irradiating laser energy at locations where the base layer has been delivered.

The method of claim 31 or 32, further comprising printing the base layer and / or the liner via three-dimensional (3D) printing techniques.

The method of any one of claims 31-33. wherein fixing the cover layer comprises direct irradiation of laser energy only at locations where the cover layer overlaps the liner.

The method of claim 34, wherein fusing the cover layer ensures that the liner does not become porous at locations where laser energy is applied directly.

The method of any one of claims 31 to 35, wherein material for the base layer and the cover layer comprises Carbon Fiber Reinforced Polymer (Carbon Fiber Reinforced Polymer, CFRP) comprising thermoplastic material and thermoplastic liner material.

A computer program product comprising instructions which, when executed by a computer, cause the computer to perform steps of the method of any one of claims 19-36.

A system for providing an apparatus according to any of the preceding claims 1-12 comprising: an Automated Fiber Placement (AFP) machine comprising a kinematic chain of actuators and rigid bodies; an end effector comprising a dispensing unit that delivers material; and a laser that emits laser energy that confirms the material; and a controller that operates the end effector to function in accordance with the instructions in the computer program product of claim 37.