Abstract:
An ultrasonic ice detector that can be mounted directly to the skin of an aircraft includes a transducer that is coupled to the interior surface of the skin, and transmits acoustic vibrational energy through the skin. A reflector bar having a reflector surface is mounted on the interior surface of the skin at a location spaced from the transducer and is effective to reflect acoustic energy back to the transducer. The reflector bar is raised from the interior surface and preferably has a width equal to the width of the acoustic wave that is generated by the transducer at the reflector location. The transducer and reflector are non-intrusive and do not alter the aircraft skin structural integrity. The arrangement provides an accurate, responsive sensor for determining presence of ice or other contaminants on the exterior surface of the skin.

Description:
CROSS REFERENCE TO RELATED APPLICATION  
       [0001]    Reference is made to U.S. patent application Ser. No. 08/651,638, filed May 26, 1996 for ACOUSTIC CHANNEL FOR CONTAMINANT DETECTION. 
     
    
     
       BACKGROUND OF THE INVENTION  
         [0002]    The present invention relates to a wave transmitter/receiver and wave reflector which can be mounted directly to the interior surface of the skin of the aircraft, and does not depend upon the use of vibrating plates or other separate sensors that require modification of the aircraft surface.  
           [0003]    The use of ultrasonic contaminant detectors is described in U.S. Pat. No. 5,629,485, where the orientation of transmitter and receivers onto a plate or sheet is taught, and a guided wave is transmitted through the sheet. The receiver receives a signal from the sheet and the presence of a contaminant on the sheet, such as ice, can be determined by the characteristics received of the wave or signal.  
           [0004]    Additionally, U.S. patent application Ser. No. 08/651,638, filed May 26, 1996 discloses a contaminant detection device that includes a plate that can be mounted onto the skin of an aircraft, and which includes a reflecting groove formed in the plate at a location spaced from a transducer/receiver.  
           [0005]    U.S. Pat. No. 5,729,508 discloses an environmental seal for an acoustic transducer that can be used for transmitting ultrasonic vibrations in ice detecting systems such as the present invention.  
           [0006]    U.S. Pat. No. 4,461,178 also discusses contaminant detection using guided waves.  
         SUMMARY OF THE INVENTION  
         [0007]    The present invention relates to an ultrasonic ice detection system which can be mounted directly onto interior surfaces of an aircraft skin or outer wall, or on a component of an airborne vehicle, such as the inlet of a turbine engine, or on other structures, without having a separate sheet or plate installed. The sensor is non-intrusive in the form disclosed. The invention uses a transmitter/receiver oriented to transmit vibrations at a particular phase velocity. The vibration will propagate through the aircraft skin or wall, and a reflector bar is located at a predetermined position to provide an adequate reflected wave. The reflector location is selected to optimize performance.  
           [0008]    Both the transducer assembly and the reflector bar are secured to the interior surface of the skin of an aircraft, so that the sensor components mount interiorly of the aircraft. There is no need for providing a separate waveguide plate that requires alteration of the aircraft structure or the aircraft skin. There is also no need to cut reflective surfaces on the aircraft or engine housing wall itself. Providing an acoustic energy path along the skin or wall that is free of rivets or other attached structures insures propagation and the ability to detect changes in vibrational frequency and/or amplitude due to contaminants, such as ice, bonding to exterior surfaces of the aircraft skin.  
           [0009]    In one aspect of the invention, as shown, the moveable slat at the leading edge of the wing, which is used for changing lift characteristics of the wing, is illustrated as an exemplary form of the invention. The exemplary form shows that the acoustic energy can be transmitted along curved wall structures to the reflector bar, and as well as being capable of reflecting acoustic energy along flat plates.  
           [0010]    Parameters for determining the height and depth of the reflector can be optimized by experimental procedures, or by finite element analysis or boundary element analysis utilizing numerical methods. 
       
    
    
     BRIEF DESCRIPTION OF THE DRAWINGS  
       [0011]    [0011]FIG. 1 is a perspective view of a portion of a typical leading edge slat of a wing of an aircraft having a detection system made according to the present invention installed thereon;  
         [0012]    [0012]FIG. 2 is a side view of the leading edge slat shown in FIG. 1;  
         [0013]    [0013]FIG. 3 is a sectional view illustrating an air duct passage that provides for a rivet free path for acoustic energy from the transducer of the present invention;  
         [0014]    [0014]FIG. 4 is a schematic representation of the transducer and reflector assembled on the internal surface of aircraft skin; and  
         [0015]    [0015]FIG. 5 is a schematic representation of the propagation path of acoustic energy from the transducer of FIG. 4. 
     
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS  
       [0016]    Referring to FIG. 1, a leading edge slat assembly  10 , for an airfoil or wing, comprises an aircraft structure that has an exterior skin or wall  12 , manufactured, in this instance, to include a planar top plate section  14 , and a curved airfoil leading section  16  that has a trailing end flat portion  18  extending rearwardly from the leading edge. The planar portion  18  is reinforced with a bulk head  20  that is made to extend up to the plate section  14 , and it has a bent leg section  22  that is riveted to the plate section  14  with suitable flush rivets in openings  24 . The curved airfoil section  16  portion defines an interior chamber  26  which has a concave interior surface  31 , in which a hot air duct  28  used for deicing purposes is provided. This duct  28  is called a “piccolo” tube because it will have a number of openings in desired locations, such as those indicated at  30 , that will permit hot air to flow along the interior surface  31  of the chamber  26 , and through recesses in the junction of the outer skin section  14  and the bent leg section  22  that form hot air ducts  34  shown in FIG. 3. The ducts  34  shown in FIG. 3 are greatly enlarged. The rivets  24 A in opening  24  are illustrated and the ducts  34  are between the rivets. The air ducts provide a channel for directing acoustic energy that is free of vibration reflecting structures, such as rivets.  
         [0017]    An ultrasonic or acoustic energy transducer assembly comprising a transmitter/receiver  39  and a mounting housing indicated generally at  38  has an end surface  40  bonded and secured intimately with the under surface of the flat plate section  14 , adjacent to the bent lip  22 , and in a position so that the acoustic energy transmitted or generated by a piezoelectric or other suitable ultrasonic transmitter/receiver  39  in the transducer assembly  38  will be propagated through one or more of the ducts  34  and across and along the concave wall section  16 . Magnetostrictive elements and electromagnetic acoustic transducers can be used as well.  
         [0018]    An acoustic energy reflector discontinuity comprising a bar  44  is securely and intimately adhered to the interior surface  31  adjacent or on the flat portion  18  of the aircraft skin or wall at a selected location in the path of propagation of ultrasonic vibration from the transducer assembly  38 . The reflector bar  44  has a curved reflector surface  45 . The surface  45  is perpendicular to the interior surface  31 . The height of bar  44  is shown schematically at  60  in FIG. 4, and also shown with a depth  62  that is parallel to the direction of wave propagation. The width  66  of energy discontinuity reflector bar  44  measured perpendicular to the direction of wave propagation also is selected to provide optimum reflection and sensitivity to contaminants on the exterior surface  11  of the aircraft skin  12 .  
         [0019]    The transducer assembly  38  is connected to a computer based control and sensing circuit  46  which is on board the aircraft. The control computer is programmed to excite the transducer  39  to launch acoustic energy or vibration that is transmitted through the skin  12 , and to alternately receive signals from the transducer  39  when it is vibrated from returning or reflected energy in the same manner as those explained in U.S. patent application Ser. No. 08/651,638, filed May 26, 1996, and using a transducer that is assembled and oriented similarly to that shown in U.S. Pat. Nos. 5,729,508 and 5,629,485.  
         [0020]    Thus, the transducer is controlled to transmit a pulse or burst of acoustic energy and then be still for a time to receive a reflected vibration. The presence of contaminants on the surface can be determined by examining the characteristics of the signal reflected and received at the transducer relative to the transmitted signal.  
         [0021]    Again, it can be seen in FIGS. 1 and 2 that the transducer assembly  38  and the acoustic energy reflector discontinuity  44  are on the interior surfaces of the skin or wall to be sensed. The transducer and the reflector are both bonded in place with suitable adhesives, or can be riveted or otherwise fastened in place. Flush head rivets are used so that no protrusions into the air stream exist, and no notches or other fitting modifications have to be made to the exterior of the aircraft skin.  
         [0022]    [0022]FIGS. 4 and 5 are schematic representations of the aircraft skin illustrated generally at  50  having an interior surface  52  on which a transducer assembly  54  is mounted, and illustrate the principals of the present invention. The wall or skin  50  may be an aircraft body, turbine engine inlet, a separate structure such as a high tower or a bridge, or any other structure exposed to icing conditions. The primary use envisioned is for airborne vehicles.  
         [0023]    The transducer assembly  54  is a transmitter and receiver and is mounted on a wedge  56  that transmits the energy at a selected angle relative to the interior surface  52  of the skin  50  and obtain a desirable efficiency of operation. The transducer assembly  54  is also mounted at a suitable angle relative to the plane of the skin, as shown. An acoustic energy reflector discontinuity, comprising a bar  58 , is mounted at a distance spaced from the transducer  54  and will reflect acoustic energy back to the transducer receiver section to receive the reflected vibrations and provide the signals to the computer control  46  for analysis. The height and depth of the reflector bar  58  are represented at  60  and  62 , and depending on factors such as the frequency of transmission and the like, these dimensions may be selected by experimental procedures, or the dimensions can be developed using numerical methods such as finite element analysis or boundary element analysis to determine the proper size relationship of the bar for optimum performance. The cross section profile of the reflector  58  can vary depending on the wave type and/or mode. While a rectangular cross section is shown, other examples could be triangular, rhombus, square or semi-cylindrical.  
         [0024]    [0024]FIG. 5 illustrates the width of the reflector  58 , and it also shows that the surface  64  which faces the transducer  54  is curved into an arc centered on the transducer, across the width of the reflector  58 . The width is represented by the double arrow  66 . In FIGS. 1 and 2, the curved edge surface is indicated at  45 , and faces the transducer  38 . The reflecting surface  64  extends outwardly from the interior surface of the wall or skin. The transducer  54  shown schematically in FIG. 5 is intimately bonded to the interior surface  52  of the wall or skin, and the reflector bar  58  is bonded securely as well. The reflector can be an integral surface discontinuity such as a rib or groove formed from or formed into the wall material. The curve of the surface  64  is non planar and can be concave as shown, or some other arbitrary shape that functions to reflect and focus acoustic energy towards the receiver.  
         [0025]    The distance from the transducer  54  to the reflector bar  58  is represented by the arrow  70 , and in the case of a concave reflector surface  64  as shown in FIG. 5, forms the radius of curvature of the reflecting surface  64  for increasing efficiency by providing a focusing effect of the reflected wave. The wave path of the acoustic beam of vibrational energy is indicated by the lines  71 .  
         [0026]    The width of the reflector bar represented by the double arrow  66  is selected for maximum efficiency, so that the width substantially equals the acoustic beam width at the position where the acoustic wave front and the reflector bar meet. For a bulk wave, this width can be given as a function of transducer geometry and frequency. For a circular transducer, the equation for guided waves is given in  Rayleigh and Lamb waves, Physical Theory and Applications , I. A. Viktorov, Plenum Press, New York, 1967.  
         [0027]    Thus, by orienting the reflector at a selected distance from the transducer, and insuring that the generated acoustic energy is not reflected from rivets or other random discontinuities in the wall or skin, a sensitive detector for detecting contaminants on the exterior surface of the wall or skin of an aircraft or other structure is provided. Rivets tend to scatter energy and random discontinuities will not provide optimum performance that can be achieved with a properly designed and positioned reflector.  
         [0028]    The attachment method for the reflector to the interior surface of the wall or skin should address two criteria. First, the attachment method should provide acoustic coupling that is adequate between the reflector and the wall or skin. This can be accomplished by traditional liquid couplants, dry couplants, or adhesive couplants. The couplant thickness should be thin enough to reduce acoustic losses across the interface between the surface of the skin and the transducer. Secondly, the attachment method must provide the required mechanical stability. Rivets and/or external clamping can be used to hold the reflector and the couplants in place. The reflector will reflect the acoustic energy wave back to the transducer, where the transmitter/receiver element detects changes in the reflected wave from the transmitted wave, and this provides an indication of changes in the surface conditions on the exterior of the skin.  
         [0029]    The transducer and reflector mount on the interior of the aircraft structure and are thus non-intrusive and do not affect airflow across the aircraft exterior. Use of the invention results in no reduction in aerodynamic efficiency or aircraft performance. In an example, an acoustic path between the reflector and the transducer is approximately 12 inches on a wing leading edge slat. The reflector material is preferably selected to match that of the aircraft skin, so expansion and contraction characteristics are the same and the acoustic coupling of the reflector is excellent. The reflector surface in contact with the skin is machined to match the contours of the airfoil or other structure at the location where it is installed. If mounted on a curved concave or convex surface, the reflector surface will be curved. This will reduce the bond layer thickness between the reflector and the aircraft skin so that the bonding is not a substantial deterrent to transmission of ultrasonic energy. The acoustic bond between the reflector and the skin is preferably made with high strength adhesive capable of withstanding extreme temperatures and well known in the art. The selected adhesive should also match well with the temperature environment. As stated, rivets can also be used, as can press fit nuts that are assembled into attachment holes with screws, to hold a reflector in place along with the adhesive. If fasteners are used, they must be of the flush mounted type in order to avoid disturbance of the airflow over the exterior aircraft structure.  
         [0030]    The transducer  38  has a mounting wedge so the piezoelectric element is positioned at a desired angle. Pairing of frequency and phase velocity of the acoustic wave makes it possible to differentiate between types of particles, such as water and ice on the surface and makes optimization of contaminant detection a reality. By selecting the appropriate frequency range of transmission of acoustic energy, which can be determined analytically by knowing the configuration of the skin or wall, a “Lamb” wave can be generated in the skin. The acoustic wave will resonate and will be reflected back by the reflector bar. The frequency of the acoustic vibration is selected to match the geometry of the mounting locations on the aircraft skin. Frequencies in the range of 0.5 MHz to 3 MHz are satisfactory for the application disclosed. By selecting frequency of operation, different densities of contaminants can be detected. The single transducer illustrated can be used for both transmitting and receiving acoustic vibrations, for example by having intermittent operation controlled by the computer based controls  46  so that a transmission would occur in a burst and the transducer would then be a receiver to receive reflected waves to provide an output. A separate transmitter and separate receiver also can be used to form the transducer assembly. The transmitter and receiver will be adjacent and together form a transducer assembly.  
         [0031]    Piezoelectric sensor elements are capable of transmitting energy or vibration at selected frequencies when energized with an external signal, controlled by computer based controls  46 , and can generate an electric signal from reflected vibrations that are received. The techniques of transmitting and receiving acoustic vibrations are well known, and include other vibration generators, as stated.  
         [0032]    Although the present invention has been described with reference to preferred embodiments, workers skilled in the art will recognize that changes may be made in form and detail without departing from the spirit and scope of the invention.