• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    An aircraft, external aircraft loudspeaker systems, and methods for projecting sound waves from outside an aircraft are provided. An aircraft comprises an outer skin membrane, a vibratory actuator and a controller. The outer skin membrane has an outer surface that defines an outer boundary of the aircraft. The vibratory actuator is coupled for vibration common to the outer skin membrane. The controller is operatively coupled to the vibratory actuator and is adapted to generate control for the vibratory actuator from audible content to be projected from the outer surface. The controller is further adapted to transmit control to the vibratory actuator. The vibratory actuator is designed to vibrate in response to the receipt of the command.
    公开号:FR3035762A1
    申请号:FR1653473
    申请日:2016-04-20
    公开日:2016-11-04
    发明作者:Michael Lucas；Michael Brinley；Kristopher Lynch
    申请人:Gulfstream Aerospace Corp；
    IPC主号:
    专利说明:

    [0001] [0001] The technical field relates generally to an aircraft with external loudspeakers and more particularly concerns an aircraft with external loudspeakers which comprises coupled vibratory actuators. to outer film membranes of the aircraft.
    [0002] BACKGROUND [0002] A conventional passenger aircraft comprises film membranes that define an outer periphery of the aircraft. These conventional aircraft do not usually include audio speakers due to the difficulties of incorporating conventional audio speakers into the aircraft. For example, a conventional loudspeaker may be mounted outside the skin membrane but such a system increases aerodynamic drag and reduces the range / efficiency of the aircraft. In a similar manner, these conventional speakers may be mounted in the film membrane but an opening is needed to expose the conventional speaker cone to the environment. Such openings are difficult to create and reduce the structural integrity of the film membrane. In addition, these conventional loudspeakers are usually unable to withstand the environmental and operational conditions of the aircraft. As such, it is desirable to develop aircraft and external aircraft speakers. which do not increase drag or do not require additional openings in the skin membrane. In addition, other desirable features and features will be apparent from the summary and the following detailed description and appended claims considered in conjunction with the accompanying drawings and this background.
    [0003] SUMMARY OF THE EMBODIMENTS [0004] Various non-limiting embodiments of aircraft systems and aircraft exterior speakers are disclosed herein. In a first nonlimiting embodiment, an aircraft comprises but is not limited to an outer skin membrane, a vibratory actuator and a controller. The outer skin membrane has an outer surface that defines an outer boundary of the aircraft. The vibratory actuator is coupled for vibration common to the outer skin membrane. The controller is operatively coupled to the vibratory actuator and is adapted to generate control for the vibratory actuator from audible content to be projected from the outer surface. The controller is further adapted to transmit control to the vibratory actuator. The vibratory actuator is adapted to vibrate in response to receiving the control. In a second non-limiting embodiment, an aircraft exterior speaker system includes but is not limited to an outer skin diaphragm. , a vibratory actuator and a controller. The outer skin membrane has an outer surface designed to define an outer boundary of a section of an aircraft. The vibratory actuator is coupled for common vibration to the outer skin membrane and the vibratory actuator is an electromagnetic driver or a piezoelectric actuator. The controller is operatively coupled to the vibratory actuator and is adapted to generate control of the vibratory actuator from audible content to be projected from the outer surface. The controller is further adapted to transmit control to the vibratory actuator. The vibratory actuator is moreover designed to vibrate in response to the reception of the control. In a third nonlimiting embodiment, the method for projecting sound waves from outside an aircraft includes but does not occur. not limited to receiving inputs from a plurality of sensors and generating commands for a vibratory actuator. The commands are received at a controller from a plurality of sensors of the aircraft. The commands are generated for a vibratory actuator coupled for vibration common to an outer skin membrane of the aircraft. The controls are further generated from audible content to be projected from an outer surface of the outer skin membrane. The commands 5 are also generated from the inputs received from the plurality of sensors. BRIEF DESCRIPTION OF THE DRAWINGS [0008] The advantages of the present invention will be appreciated directly by the fact that it is better understood by reference to the following detailed description considered in connection with the accompanying drawings, in which: [0009] FIG. 1 is a perspective view illustrating a non-limiting embodiment of an aircraft according to the recommendations of the present disclosure; [0010] FIGS. 2 and 3 are perspective views illustrating non-limiting embodiments of exterior loudspeaker sections of the aircraft shown in FIG. 1 15 according to the recommendations of the present disclosure; [0011] FIG. 4 is a side view illustrating a non-limiting embodiment of the exterior loudspeaker section of the aircraft shown in FIG. 1; and [0012] FIG. 5 is a flowchart illustrating a non-limiting embodiment of a method performed by the controller of FIG. 1 according to the recommendations of the present disclosure. DETAILED DESCRIPTION [0013] The following detailed description is given merely by way of example and is not intended to limit the invention or application and uses of the invention. In addition, the intention is not to be related to a theory presented by the preceding background or the following detailed description. Various non-limiting embodiments of aircraft systems and external aircraft speakers are disclosed by this document. In some embodiments, the aircraft comprises a vibratory actuator (such as electromagnetic drive coils, piezoelectric actuators) attached to a film membrane of the aircraft. The vibratory actuator is on board the outer surface of the film membrane, so that external openings or protuberances are not required to install the vibratory actuator. A controller sends commands to the vibratory actuator to cause the film membrane to vibrate according to a desired audible content. The vibration of the film membrane couples with the air in the environment around the aircraft to create an audible sound to those near the aircraft. Consistently, the aircraft and aircraft speaker systems allow the aircraft skin membrane to act as a speaker cone without the inconvenience associated with the installation of conventional exterior loudspeakers. A better understanding of the aircraft systems and external loudspeakers the aircraft can be obtained by studying the illustrations accompanying this application while studying the detailed description that follows. [0015] FIG. 1 is an isometric view illustrating a non-limiting embodiment of an aircraft 100 according to the recommendations of the present invention. The aircraft 100 includes an outer skin membrane 102, external loudspeaker vibratory actuators 104, an amplifier 105, a controller 106, a plurality of sensors 108, and a remote communication device 109. The outer skin membrane 102 has an outer surface which defines an outer limit of the aircraft 100 which comes into contact with an external air flow when an aircraft 100 is flying in the air. In the example given, some sections of the outer skin membrane 102 are made of aluminum strips and some sections of the outer skin membrane 102 are made of composite materials. It should be noted that other materials suitable for theft may be incorporated without departing from the scope of the present disclosure. The outer skin membrane 102 defines an outer surface of various parts of the aircraft such as a body-to-body fairing 110, wings 112, horizontal outriggers 114, and engine housings 116, such as those with ordinary skill in the aircraft. technical will appreciate it. The vibratory actuators 104 may be any vibratory actuator which is capable of exciting the outer skin membrane 102 to radiate sound outside the aircraft 100. For example, the vibratory actuators 104 may be an electromagnetic pilot or a piezoelectric actuator. In the example given, vibratory actuators 104 are panel drivers such as the DAEX3OHESF-4 model exciter available from DAYTON AUDIO in Springboro, OH. The vibratory actuators 104 receive signals from the controller 106. The signals 5 comprise instructions that correspond to the audible content that a user wishes to project in the form of audible compression waves 117 from the aircraft 100. [0017] Vibratory actuators 104 are coupled for common vibration to outer skin diaphragm 102 to define exterior loudspeaker sections 118. In its form used herein, the term "coupled for common vibration" is defined as the coupling of outer skin diaphragm 102 to the driven section of the vibratory actuators 104 so that these two components vibrate together substantially as a single component. This coupling causes the film membrane 102 to be excited with a content of frequency substantially similar to the excitation frequency of the driven section of the vibratory actuators 104 by the controller 106. The vibratory actuators 104 may be linked, riveted, glued, screwed, or attached or otherwise rigidly affixed to the skin membrane 102. In some embodiments, the vibratory actuators 104 may be attached to a plate which is attached to the skin membrane 102. In some embodiments, the vibratory actuators 104 may be embedded in a composite material. In the example given, the vibratory actuators 104 are mounted so that the driven section of the vibratory actuators 104 actuate the normal of the film membrane 102. In the example given, the sections of loudspeakers 118 are exterior sections of a winged body fairing 110, wings 112, horizontal stabilizers 114, and 25 of engine housings 116. It should be noted that the external loudspeaker sections 118 can be incorporated at the other sections of the aircraft 100 without departing from the scope of the present invention. The placement of loudspeaker sections 118 in any given aircraft may be influenced by the material of the skin membrane 102 at the section, whether the section is a flammable fluid zone, or the current or wiring is available directly. in this section or any other consideration of this kind. For example, the sections of the skin membrane 102 which are made of composite materials and which do not define a flammable fluid zone are well suited for the exterior loudspeaker sections 118. The mechanical strength of a composite is conventionally less than the mechanical strength of the aluminum and the energy requirement for the actuation of a composite material is therefore usually less than the energy requirement for actuating an aluminum material. Referring now to FIG. 2, a non-limiting example of a section of external speakers 118A is shown in cross-sectional view. In the example given, the outdoor loudspeaker section 118A is incorporated in a body wing fairing 110. The outer skin membrane 102 at the outer loudspeaker section 118A is a honeycomb composite material. . The honeycomb composite material comprises at least one layer of repeating column hexagonal cells sandwiched between an inner layer 126 and an outer layer 128. The inner layer 126 defines an interior cavity of the aircraft 100, such as The outer layer 128 defines the outer surface of the skin membrane 102 which is exposed to the environment. The vibratory actuator 104 of the external loudspeaker section 118A is attached to an inner surface of the inner layer 126 of the film membrane 102. For example, the vibratory actuator 104 may be attached to the inner layer 126 by a layer 20 of glue. A control wire or interconnect 122 is connected between the vibratory actuator 104 and the amplifier 105 to receive amplified sound content signals from the controller 106. [0021] Referring now to FIG. 3, a non-limiting example of a section of external speakers 118A is shown in cross-sectional view. In the given example, a section of external loudspeakers 118B is incorporated at the wings 112 and horizontal stabilizers 114. The external loudspeaker section is similar to the outdoor loudspeaker section 118A, where numbers identical refer to identical components. The vibratory actuator 104 of the external loudspeaker section 118B, however, is embedded in one or more hexagonal cells 124.
    [0004] For example, the vibratory actuator 104 may be placed in the hexagonal cell during the laying of the composite material and processed in place during the manufacture of the outer skin membrane 102. [0022] Referring now to FIG. 4, a non-limiting example of a section of external speakers 118C is shown in cross-sectional view. In Example 5 given, the external loudspeaker section is incorporated at the 118C 116 motor housing. The 118C outdoor loudspeaker section is similar to the outdoor loudspeaker section 118A, where identical numbers reference to identical components. The skin membrane 102, however, is formed of aluminum material and the vibratory actuator 104 is attached to a plate 130. The membrane 102 may be made of any type of metal or laminated material. The plate 130 is then attached to the skin membrane 102. The plate 130 may be made of any material in any form suitable for mounting the vibratory actuator 104 on the skin membrane 102. It should be noted that Any of the configurations of the exterior loudspeaker sections 118A-C may be incorporated into any section of the aircraft 100 without departing from the scope of the present disclosure. For example, any of the exterior loudspeaker sections 118A-C may be positioned at any of the sections defining the wings 112, horizontal stabilizers 114, engine housings 116, or wing shroud. The amplifier 105 receives audio signals generated by the controller 106 and amplifies the audio signals to a level sufficient to drive the vibratory actuators 104 with sufficient power to cause the outer skin membrane 102 to radiate waves. compression 117 corresponding to the audio signals. The amplifier 105 is coupled to a current source (not shown) and to the controller 106. In some embodiments, an amplifier 105 is centrally positioned in the aircraft 100 to power multiple vibratory actuators 104. In such forms of the amplifier 105, separate speaker cables are connected between the amplifier 105 and each vibratory actuator. In some embodiments, separate amplifiers 105 are placed near each vibratory actuator 104 to reduce the speaker wire passages in the aircraft 100 and utilize the existing wiring capable of carrying digitized audio signals.
    [0005] In some embodiments, audio signals are sent wirelessly to amplifiers 105, which can receive current from nearby components. For example, amplifiers 105 in the wings 112 can tap into the light feed lines on the flanges 112. The controller 106 is operatively coupled to the vibratory actuator 104 via the amplifier 105. using an interconnection 122. The controller 106 is designed to generate commands for the vibratory actuator 104 from audible content to be projected on the outside of the aircraft 100. The audible content may be music, speech, alarms, sounds or other content usually projected by conventional loudspeakers. In some embodiments, the controller 106 is adapted to perform the operations described hereinafter. The controller 106 may include any combination of software and hardware. For example, the controller 106 may comprise an application specific integrated circuit (ASIC), an electronic circuit, a processor (shared, dedicated or group), and a memory that executes one or more software or firmware programs. , a combined logic circuit and / or other suitable components that provide the described functionality. In some embodiments, various operations performed by the controller 106 may be saved as instructions a non-transitory computer readable medium. The instructions may be executed to cause one or more processors to perform the operations described hereinafter. In some embodiments, the controller 106 includes multiple separate control modules operating together to perform the operations described hereinafter. In some embodiments, the controller 106 is integrated with other controllers of the aircraft 100, such as a flight control computer of the aircraft 100. [0027] The sensors 108 include alarm sensors, proximity sensors, cabin management sensors, and other sensors adapted for the aircraft 100, as will be generally appreciated by those of ordinary skill in the art. The remote communication device 109 may be a satellite transmitter / receiver, a wireless Internet transceiver, a cellular communications transmitter / receiver, or any other suitable remote communication apparatus. Referring now to FIG. 5, a non-limiting embodiment of a method 200 of using an external aircraft loudspeaker system is presented in flowchart form. The operations of the method 200 are performed by the controller 106. The controller 106 receives sensor inputs 108 in the operation 202.
    [0006] For example, the controller 106 may receive inputs indicative of a distance between a wall and a wing tip from a proximity detector in the operation 202. [0029] The controller 106 determines whether there are remote users to notify sensor inputs in operation 204. When there are remote users to be notified, controller 106 generates a report for remote users in operation 206. For example, aircraft 100 may communicate with an application on a remote device (such as an aircraft owner's mobile phone) via satellite communication, wireless communications, or other suitable means of communication. In some embodiments, the controller 106 may generate an alarm notification to be transmitted to the remote user by remote communication device 109 in response to the intruder detection near the aircraft 100. [0030] Controller 106 receives inputs from the remote user in operation 208. For example, controller 106 may receive commands or voice data from the application from the mobile phone operated by the remote user. In some embodiments, the owner may speak in the mobile phone in response to the generated report, so that the owner can communicate with persons located near the aircraft 100 by sending audio signals to the controller 106 by communication device In some embodiments, the application may send location data to controller 106, which may further be adapted to broadcast music or courtesy phrases in response to receiving input commands. from the application indicating that the remote user is approaching the aircraft 100. In some embodiments, the music or the courtesy formulas may be preselected by the owner of the aircraft 100. [0031] When There are no remote users or when a remote user has to be notified of the sensor input, the process 200 proceeds to the ope The controller 106 generates commands for the vibratory actuators 104 starting from the inputs received in the operation 210. For example, the generated commands may be based on the input of the sensor or the input from the sensor. remote user for audio projection on the exterior of the aircraft 100. In some embodiments, the controller 106 generates commands from the audio signals received from the remote user to facilitate communication between the user. located remotely and people located near the aircraft. In some embodiments, the controller 106 is also designed as a security system and the method 200 describes the operation of the security system. For example, the security system may receive signals from sensors and systems in the aircraft 100 to determine if conditions in and around the aircraft 100 indicate a risk of theft or deterioration, such as possessing ordinary skills in the art will appreciate it. The controller 106 is further configured to generate the commands from determinations made by the security system in the operation 210. For example, when the controller 106 receives signals from proximity sensors and determines that people are near by of the aircraft 100 while the security system feature is active, the controller 106 can generate commands for the vibratory actuator 104 to project audible content. This audible content may be alarm sounds, a prerecorded message or other appropriate warnings to be heard by potential thieves or vandals located outside the aircraft 100. In some embodiments the controller 106 is designed as a collision avoidance system with the tugs and the method 200 describes the operation of the collision avoidance system with tugs. For example, the controller 106 may be designed to interface with sensors near the sensors 108. In some embodiments, the tug collision avoidance system is similar to the system disclosed in the US patent application. 14 / 599,758 jointly outstanding filed on January 19, 2015 which is thus incorporated herein by reference in its entirety. In some embodiments, the controller 106 is designed to generate the commands based on the proximity of a wing tip of the aircraft 100 to an object such as a shed wall. Accordingly, the tug driver may be equipped with in-ear towing warning devices without the need for additional equipment. For example, the controller 106 can determine a distance between the tip of the wing and the wall. The controller 106 may then generate commands for speech which indicates the distance (such as, for example, "1.50m", "5cm", etc.) or for making sounds or beeps at intervals dictated by the distance. In some embodiments, the controller 106 is further adapted to receive signals from a pilot's helmet to generate a command from the signals received from the pilot's helmet. For example, a microphone placed on the pilot's helmet may be among the plurality of sensors 108 used by the controller 106 in the method 200. The pilots and the ground crew often communicate on channels specified by helmets but the rest staff can be connected to different channels on which the driver is not broadcast. In such situations, when the pilot detects an impending collision or a dangerous situation, the pilot may broadcast warnings or instructions through external speaker sections 118. In some embodiments, the pilot may have a button or to a separate input device which generates a warning or alarm tone from the outdoor speaker sections 118. In some embodiments, the controller 106 is further configured to generate the commands from maintenance instructions to be sent to the ground crew during maintenance operations. For example, some hatches and hose connections require unique opening / closing procedures for a specific aircraft model that are not always known or intuitive for the ground crew. Conventional procedures include searching the aircraft manual to identify these unique procedures. By announcing these instructions from the outdoor speaker sections 118, such additional search may be reduced or deleted. In some embodiments, the controller 106 is further configured as a cabin management system that detects the power state of the devices and systems of the aircraft. For example, the controller 106 may be adapted to receive a coffee maker signal or interior lights from the booth indicating whether the coffee maker or lamps inside the booth are on or off. The controller 106 may further be designed to generate commands for announcing which devices and systems are in the "on" power state in response to the detection of an occupant exiting the aircraft. For example, the controller 106 can detect the absence of occupants in the aircraft itself by occupancy and motion sensors 5 and can generate commands to announce that the coffee maker has been left on while the door of the aircraft 100 is closed. In some embodiments, the controller 106 is further configured to generate the commands from an active noise suppression. For example, suppressing jet engine noise by using the external loudspeaker section 118 at the engine casings 116 may be desirable to reduce the noise generated by the aircraft 100 in the areas near the airports during the flight. take off and landing. Further active noise suppression of the cell can also be integrated, as with the external loudspeaker section 118, at the wing-to-body fairing 110. In some embodiments, the controller 106 is further adapted to generate commands from noise masking to be generated by the external speaker sections 118. In some embodiments, the controller 106 is further configured to generate the commands from the deterrent sounds for the birds. to project from the outer surface of the outdoor loudspeaker section 118. The bird deterrent sounds deter the birds from landing on the aircraft 100 while parked and flying in an aircraft course. 100 during the flight. For example, the controller 106 may be adapted to emit sounds from the outdoor speaker sections 118 at regular intervals or in response to the detection of birds by the sensors 108. During the flight, the controller 106 may be configured to broadcast sounds from external loudspeaker sections 118 from avian radar components in the sensors 108. While at least one exemplary embodiment has been presented in the preceding detailed description of the invention, it should be noted that a large number of variations exist. It should also be noted that the exemplary embodiment or exemplary embodiments are only examples and are not intended to limit the scope, applicability or configuration of the invention in any way. Instead of this, the foregoing detailed description will provide those skilled in the art with a practical roadmap for implementing an exemplary embodiment of the invention. It is understood that various changes may be made to the function and arrangement of the elements described in an exemplary embodiment without departing from the scope of the invention as set forth in the appended claims.
    权利要求:
    Claims (20)
    [0001]
    REVENDICATIONS1. An aircraft, comprising: an outer skin membrane having an outer surface that defines an outer boundary of the aircraft; a vibratory actuator coupled for vibration common to the outer skin membrane; and a controller operatively coupled to the vibratory actuator and adapted to generate control for the vibratory actuator from audible content to be projected from the outer surface and further adapted to transmit control to the vibratory actuator; Vibratory shareholder being designed to vibrate in response to the receipt of the order
    [0002]
    An aircraft according to claim 1, wherein the outer skin membrane forms at least a portion of an engine casing, a body-to-body fairing, a horizontal stabilizer, a wing of the aircraft or their combinations.
    [0003]
    An aircraft according to claim 1, wherein the outer skin membrane is a composite material formed of a honeycomb structure and wherein the vibratory actuator is embedded in a cell or cells of the nest structure. bee.
    [0004]
    An aircraft according to claim 1, wherein the outer skin membrane has an inner surface and wherein the vibration actuator is attached to the inner surface of the outer skin membrane.
    [0005]
    An aircraft according to claim 1, wherein the vibratory actuator and an electromagnetic pilot or a piezoelectric actuator. 14 3035762
    [0006]
    An aircraft according to claim 1, wherein the controller comprises a component of a security system and wherein the controller is further adapted to generate the command from a threat detected by the security system. 5
    [0007]
    An aircraft according to claim 1, further comprising a pilot's headset microphone coupled to the controller and wherein the controller is further adapted to receive signals from the pilot's headset microphone and to generate the command from the signals received from the headset microphone. pilot's headset microphone. 10
    [0008]
    An aircraft according to claim 1, further comprising a remote communication device coupled to a remotely operated remote user device and wherein the controller is further adapted to generate control from the inputs of the device remote communication to facilitate communication between the remote user and persons located near the aircraft.
    [0009]
    The aircraft of claim 1, further comprising a wing with a wing tip, wherein the controller is further adapted to generate the control based on the proximity of the wing tip to a wing tip. object for sending tug driver tug warnings.
    [0010]
    The aircraft of claim 1, wherein the controller is further embodied as a cabin management system that detects a power state of aircraft devices and systems and wherein the controller is further configured to 25 generate commands to announce which devices and systems are in the "on" power state in response to detection of an occupant leaving the aircraft.
    [0011]
    An aircraft according to claim 1, wherein the controller is further adapted to generate commands from instructions and maintenance to be sent to the ground crew during maintenance operations. 15 3035762
    [0012]
    The aircraft of claim 1, wherein the vibratory actuator is coupled to the outer skin diaphragm at a motor housing and wherein the controller is further adapted to generate the controls from a suppressor. active noise of the noise generated by a jet engine of the aircraft.
    [0013]
    An exterior aircraft loudspeaker system, comprising: an outer skin membrane having an outer surface configured to define an outer boundary of a section of an aircraft; A vibratory actuator coupled for vibration common to the outer skin membrane, the vibratory actuator comprising an electromagnetic driver or a piezoelectric actuator; and a controller operatively coupled to the vibratory actuator and adapted to generate control for the vibratory actuator from audible content to be projected from the outer surface and further adapted to transmit control to the vibratory actuator, the shareholder vibratory being designed to vibrate in response to the receipt of the command
    [0014]
    The aircraft external speaker system of claim 13, further comprising a plurality of sensors and wherein the controller is further adapted to generate control from inputs received from the plurality of sensors.
    [0015]
    An aircraft external speaker system according to claim 13, wherein the outer skin membrane is a composite material formed of a honeycomb structure and wherein the vibratory actuator is embedded in a cell or cells of the honeycomb structure.
    [0016]
    The aircraft exterior speaker system of claim 13, wherein the outer skin membrane has an inner surface and wherein the vibration actuator is attached to the inner surface of the outer skin membrane. 16 3035762
    [0017]
    17. A method of projecting sound waves from an aircraft exterior, said method comprising: receiving, at a controller, inputs from a plurality of sensors of the aircraft; and generating commands for a vibratory actuator coupled to vibration common to an outer skin membrane of the aircraft from audible content to be projected from an outer surface of the outer skin membrane, wherein the control generation is based on the inputs received from the plurality of sensors.
    [0018]
    The method of claim 17, wherein the generating of commands further comprises generating commands from a threat detected by a security system. 15
    [0019]
    The method of claim 17, wherein the generating of commands further comprises generating commands from deterrent sounds for the birds to be projected from the outer surface. 20
    [0020]
    The method of claim 17, wherein the generating commands further comprises generating commands from the proximity of a wing tip to an object for sending tow warnings to a tugboat driver. 17
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    同族专利:
    公开号 | 公开日
    US9834320B2|2017-12-05|
    US20160318627A1|2016-11-03|
    DE102016107822A1|2016-11-03|
    CN106081135A|2016-11-09|
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    法律状态:
    2017-04-26| PLFP| Fee payment|Year of fee payment: 2 |
    2018-12-07| PLSC| Search report ready|Effective date: 20181207 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/697,895|US9834320B2|2015-04-28|2015-04-28|Aircraft and exterior speaker systems for aircraft|
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