• 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:
    A detachable warning, detection and anti-theft system (100) for an aircraft (10) comprises a detachable mounting device which is designed for fastening to an aircraft. The detachable mounting device contains a detection system and a warning system. The detection system can detect objects in the vicinity of the aircraft and generate a detection signal when an object in the vicinity of the aircraft is detected. The warning system can generate at least one alarm signal that is perceptible outside the aircraft.
    公开号:CH710961B1
    申请号:CH00412/16
    申请日:2016-03-29
    公开日:2019-12-30
    发明作者:Hausmann Jeffrey；Manochio Frank；Meade Jason；O'dell Robert；Lee Hancock Jimmy
    申请人:Gulfstream Aerospace Corp；
    IPC主号:
    专利说明:

    description
    Technical Field The present invention relates to a removable warning, detection and anti-theft system for an aircraft.
    Background When an aircraft is on the ground, numerous different events can occur that can damage the aircraft. Examples of such events include, but are not limited to, accidental collisions with other ground vehicles, accidental collisions with another aircraft that is either taxiing or being towed, accidental collision with fixed structures, impact on or from objects, etc.
    [0003] Systems have been proposed to integrate complex monitoring and control devices into an aircraft during manufacture. These monitoring and control devices can detect events and generate appropriate warnings that indicate that an object or person is about to come into contact with the aircraft. The cost of retrofitting an aircraft to include these monitoring and control devices in and on the aircraft is significant and would be a significant expense for manufacturers to install such monitoring and control devices. The use of on-board monitoring and control equipment also requires power to be applied to the aircraft, which, for example, complicates ground operations and aircraft movement.
    For an existing aircraft, most aircraft owners would not choose the option to upgrade their aircraft with such monitoring and control devices because the installation costs of these monitoring and control devices make this impossible.
    [0005] Therefore, it is desirable to provide a technology that can solve these problems cost-effectively. It is desirable to provide technology that detects and / or reports people or objects that approach or come into contact with the aircraft while on the ground and that records and / or reports incidents that occur on the aircraft (e.g., images an object approaching or coming into contact with the aircraft). It would also be desirable to provide technology that can generate alarm signals to provide a warning indicating that contact with the aircraft is possible if someone or something is approaching and / or is about to board the aircraft Contact. Other desirable features and characteristics of the present invention will become apparent from the following detailed description and the appended claims, taken in conjunction with the accompanying drawings and the foregoing technical field and background.
    Summary The invention provides a removable warning, detection and anti-theft system for an aircraft with the features of claim 1.
    A warning, detection and anti-theft system is provided, which contains a removable mounting device. The removable mounting device is designed for attachment to an aircraft. There is a detection system which is designed to detect objects in the vicinity of the aircraft and to generate a detection signal when an object is detected in the vicinity of the aircraft. A processor is provided which is designed to receive a detection signal from the detection system and to generate control signals; and finally a warning system is provided which is designed to generate at least one alarm signal which is perceptible outside the aircraft.
    In an advantageous embodiment, a belt is provided which is designed to be looped around a part of the aircraft, the belt comprising: a protective material to prevent damage to the part of the aircraft around which the belt is looped, and a locking mechanism that locks the belt on the aircraft to prevent the belt from being removed from the aircraft until the locking mechanism is unlocked. A battery is designed to supply electrical power for the warning, detection and theft protection system. Solar cells are integrated in the belt and designed to generate electrical energy in order to supply at least part of the electrical power.
    Brief Description of the Drawings Embodiments of the present invention will hereinafter be described in conjunction with the following drawings, in which like reference numerals designate like elements, and
    1 is a top view of an aircraft in accordance with some of the disclosed embodiments,
    2 is a perspective view of an aircraft in accordance with some of the disclosed embodiments,
    CH 710 961 B1
    FIGS. 3-6 are schematic diagrams showing a removable detection and warning system that can be mounted on an aircraft in accordance with the disclosed embodiments.
    7 is a block diagram showing electrical connections between various blocks that form a detachable detection and warning system according to an implementation of the disclosed embodiments.
    8 is a perspective view of an aircraft showing fields of view of sensors that are part of a detachable detection and warning system in accordance with some of the disclosed embodiments.
    Detailed Description In many cases, it may be difficult and / or expensive to provide permanent detection and warning systems in and / or on an aircraft. For example, if an aircraft does not have sensors (e.g. proximity sensors) or imaging devices integrated in the aircraft, it may be impractical or undesirable (e.g. expensive) to change the aircraft and incorporate these sensors / imaging devices into the aircraft. It would be desirable to provide detection and warning systems that are easy to use and are temporarily mounted on the aircraft while on the ground and then removed before the flight.
    1 is a top view of an aircraft 10 and FIG. 2 is a perspective view of the aircraft 10 according to some of the disclosed embodiments. 1 and 2 show two detachable detection and warning systems 100 attached to the aircraft 10 in accordance with some of the disclosed embodiments. In this non-limiting implementation, the detachable detection and warning systems 100 are attached to the wing tips 113 of the aircraft 10; however, in other implementations, the detachable detection and warning systems 100 may be mounted in other locations such as the engines 118, the wings 112, the tail or any other suitable location. Furthermore, any number of detection and warning systems 100 can be attached to the aircraft as desired.
    [0012] In this non-limiting implementation of the disclosed embodiments, the aircraft 10 includes a fuselage 110 in which the passengers and the cargo are located; two main wings 112 which provide the lift necessary for the aircraft 10 to fly; a fin 114 and two fin 116 used to ensure stable flight; and two engines 118 that provide the necessary thrust to propel the aircraft 10 forward. The two main wings 112 contain wing end plates 113 at the very end. Control surfaces for guiding the aircraft 10 are placed on wings 112, vertical fins 116 and side fins 114. The control surfaces can contain primary and secondary control surfaces. The primary control surfaces are operated by a pilot seated in the cockpit of the aircraft 10 and can control the ailerons 117 located on the trailing edges of the wings of the aircraft 10, the elevator controls 102 located on the fin of an aircraft 10, and the rudder 104 located on the fin. The secondary control surfaces may include spoilers 119 and landing flaps 120 provided on the trailing edges of the wings 112 of the aircraft 10.
    1 and 2, the detachable detection and warning systems 100, as described below, may each include different types of (among others) sensors, imagers, visual alarms, and audible alarms that are in and / or are mounted on an assembly device which can be attached to the aircraft (eg after the flight) (eg connected) and (eg before takeoff) removed from the aircraft. The various sensors may include motion sensors that are designed to detect motion in the vicinity of the aircraft 10. As described below, the detachable detection and warning system 100 can help protect the aircraft from impact from objects moving near the aircraft.
    3-6 are schematic diagrams showing different views of a detachable detection and warning system 100 according to the disclosed embodiments. FIGS. 3-7 each show elements that may be part of a detachable detection and warning system, and therefore FIGS. 3-6 are described below in connection with FIG. 7.
    3 is a schematic diagram showing various components of a detachable detection and warning system 100 according to an implementation of the disclosed embodiments. FIG. 4 is a schematic diagram showing the layout of detachable detection and warning system 100 before it is installed on an aircraft in accordance with an implementation of the disclosed embodiments. As described below, the detachable detection and warning system 100 can be mounted on the aircraft and used to control objects moving near the aircraft 10 when the aircraft 10 is on the ground. As used herein, an object may refer to a person or object approaching and / or coming into contact with the aircraft 10. Detachable detection and warning system 100 may be removed from aircraft 10 prior to flight.
    The detachable detection and warning system 100 includes, among other things, a detection system configured to detect objects in the vicinity of the aircraft (and / or incidents that occur near the aircraft) and a warning system that to generate an optical or acoustic alarm signal or several opti
    CH 710 961 B1 shear or acoustic alarm signals is formed, which is / are perceptible to people who are outside the aircraft. These alarm signals can provide a timely warning to ground personnel or the crew to prevent a collision with the aircraft when it is likely. The alarm signal (or signals) can serve as a warning that an incident has occurred outside the aircraft. If, for example, a vehicle drives towards the aircraft and threatens to collide with it, an alarm is generated. As described below, in both examples, a record of the incident, which includes images, is recorded in an incident report file and can be communicated to another computer. This helps reduce the time it takes to investigate incidents and can save time in identifying who or what was responsible for the damage to the aircraft. It can also provide a record of a person or vehicle approaching the aircraft, even if the aircraft has not been damaged.
    5 is a schematic diagram showing a cross-sectional view of a wing 112-1 of the aircraft 10 looking inward, with the detachable detection and warning system 100 on a wing 112-1 of the aircraft 10 in accordance with an implementation of the disclosed Embodiments is installed. 6 is a schematic diagram showing the detachable detection and warning system 100 after it has been installed on a wing 112-1 of the aircraft 10 in accordance with an implementation of the disclosed embodiments.
    A detachable detection and warning system 100 is designed or designed to be attached to the aircraft 10 to temporarily mount the detachable detection and warning system 100 to the outside of the aircraft while the aircraft is on the ground. The detachable detection and warning system 100 includes a mounting device 202 that is temporarily attached to the aircraft 10. The mounting device 202 is configured to be placed over an outer surface of the aircraft and to be looped around a part of the aircraft, such as a wing 112 or a wing end plate 113 of the aircraft. Alternatively, the detachable detection and warning system 100 can be attached to other parts of the aircraft, such as the fuselage 110, the fin 114, the fin 116, and so on a wing end plate 113 of the aircraft is pushed and then locked in position while the aircraft is on the ground. In one embodiment, the mounting device 202 is configured to be looped around part of the aircraft and may include a protective material to prevent damage to the part of the plane around which it is looped. For example, in one implementation, the mounting device 202 may be made from a padded ripstop nylon material that fits snugly around a wing of the aircraft. Padding on the inner surface of the mounting device 202 prevents the mounting device 202 from scratching an outer surface of the aircraft around which it is wrapped and in contact.
    In one embodiment, the mounting device 202 is a belt configured to be looped around a portion of the aircraft. The belt may include a fastening and locking mechanism 206 which locks the belt on the aircraft to prevent the belt from coming off the aircraft before the locking mechanism is unlocked. For example, in the embodiment shown in Figures 4 and 6, the fastening and locking mechanism 206 can be implemented as a quick release mechanism that includes clip connectors and a corresponding set of fasteners (e.g. clip connectors and / or securing tabs and buckles). To prevent the detachable detection and warning system 100 from being removed from the aircraft, in some embodiments, the detachable detection and warning system 100 may include a locking system that prevents the detachable detection and warning system 100 from being removed from the aircraft if not someone has the ability to unlock it.
    Figure 7 is a block diagram showing electrical connections between various blocks that form a detachable detection and warning system 100 in accordance with the disclosed embodiments. Fig. 7 will now be described with reference to Figs. 1-6.
    recognition system
    Sensors In one embodiment, the detection system may include multiple sensors 210. 3 and 4 include two sensors 210, in other implementations either fewer or more of the sensors may be implemented at different locations on the mounting device 202. Therefore, although the drawings show two sensors 210, it should be understood that the number and corresponding locations of the sensors are exemplary and not restrictive.
    [0022] Each sensor 210 can detect objects in the vicinity of the aircraft. The sensors 210 may include proximity sensors that detect objects in the vicinity of the aircraft, motion detection sensors that detect movement of objects in the vicinity of the aircraft, etc.
    8 is a perspective view of the aircraft 10 showing the field of view of each of the sensors 210 according to some of the disclosed embodiments. In the exemplary embodiment shown in FIG. 8, the detachable detection and warning systems 100 are arranged along the wing 112 and / or wing end plates 113 of the aircraft; however, in other embodiments, the detachable detection and warning systems 100 can be along
    CH 710 961 B1 other surfaces, such as opposite, backward facing sides of the aircraft's fin (or tail) 116, along the aircraft's fin 114 (or, in some implementations that have a T conductance configuration, along opposite sides of an upper one Fin of the aircraft), along opposite, rearward-facing sides of the wing tips, on the underside of the fuselage along the lowermost part of the fuselage, along the nose of the aircraft, along the opposite forward sides of the fin of the aircraft, along opposite forward sides of the wings and along the top of the fuselage. For example, each of the detachable detection and warning systems 100 may include a sensor 210 that has a forward field of view 812 that covers an area in front of the aircraft 10, another sensor 210 that has a side field of view 814 that has an area on the side of the aircraft 10, and another sensor that has a rear field of view 816 that covers an area behind the aircraft 10. The sensors 210 can be oriented such that their corresponding coverage areas are arranged such that they cover up to a complete 360-degree recognition (for example within a volume that is defined by the cross-sectional area of an ellipse 820) for the aircraft 10 offer, so that all objects, including people who step into the space around the aircraft 10 (for example, get close to the aircraft 10) can be recognized. In other words, the sensor cover may include any area around the aircraft, including an area that extends over, under, and next to the aircraft. As used here, the term “object” should be interpreted in a broad sense so that it refers to everything that can approach and / or come into contact with an aircraft. For example, an object can refer to any material object that can approach and / or come into contact with an aircraft.
    Specific examples of sensors 210 will now be described.
    Motion sensors Examples of motion sensors include proximity sensors 210 and motion detection sensors 210, radar sensors that detect motion near the aircraft, ultrasonic sensors that detect motion near the aircraft, infrared sensors, and / or real-time analysis of video images from those Imaging devices 220 are generated, etc.
    The motion sensors 210 are used to detect objects that are within their detection zone (e.g., within a certain area that is near the aircraft 10). The motion sensors 210 emit pulses (e.g. electromagnetic wave pulses, sound wave pulses, pulses of visible, ultraviolet or infrared light, etc.), which are directed and emitted as a wide beam onto a specific detection zone that covers the field of view of the sensor. The duration of the pulses defines a detection zone for each motion sensor. For a short period of time after each pulse is emitted by this motion sensor, waves can be reflected from an object to the sensor. The time period is approximately equal to the time required for a pulse to move from the motion sensor 210 to the detection zone and for a portion of the wave reflected from an object to the motion sensor 210 to reach the motion sensor 210. The time period enables the distance between the motion sensor 210 and an object within the detection zone to be calculated. For example, it is possible to measure the time required to reflect a pulse and use the time to calculate a distance between the motion sensor and a reflective surface of the object. For example, the distance between motion sensor 210 and the detection zone can be calculated as the speed of the sensor medium (e.g., speed of light) divided by the time delay between sending the pulse and receiving a reflected wave from an object within its detection zone.
    [0027] The types of motion sensors 210 that are used may vary depending on the implementation. In one implementation, motion sensors 210 can be implemented with sonar or ultrasonic sensors (or transceivers) that generate and transmit sound waves. These sensors receive and evaluate the echo that is reflected to the sensor. The time interval between sending the signal and receiving the echo can be used to determine the distance between the sensor and a detected object.
    However, in other implementations, motion sensors 210 may include radar sensors, laser sensors, infrared sensors, LIDAR (Light Detection and Ranging) sensors, infrared or laser range finders using a set of infrared or laser sensors, and triangulation techniques to detect an object and implemented to determine its position with respect to an aircraft, distance from the aircraft, etc. For example, in one embodiment, motion sensors 210 may be infrared sensors that include an infrared light transmitter and receiver. Short light pulses can be sent by the transmitter and if at least some light pulses are reflected by an object, the object is recognized by the receiver. Furthermore, in one implementation, information from one or more types of sensors may be used in conjunction with video data from imaging devices 220 to detect moving objects.
    The range that lies in the field of view (FOV) of the motion sensors 210 defines object detection zones for each motion sensor 210. The range that lies in the field of view of the motion sensors 210 may depend on the implementation and design of the aircraft 10 vary. In some embodiments, the field of view and range of motion sensors 210 may vary. For example, the size and location of the detection zone may vary relative to motion sensor 210 (and thus to aircraft 10).
    CH 710 961 B1
    Communication Interfaces The mounting device 202 may also include at least one wireless communication interface 240 configured to send and receive communication signals to communicate information via wireless communication links with other wireless communication interfaces (e.g., another device). Each wireless communication interface contains a wireless receiver, a wireless transmitter, and an antenna. Each wireless communication interface 240 is operationally and communicatively coupled to antennas (not shown) so that it can communicate with wireless communication interfaces over one or more of the wireless communication links (not shown). Each wireless communication interface may be coupled to a processor 250 and a power source 260, such as a battery, that provides electrical power. The wireless transmitter can communicate information (e.g., motion information, video images, etc.) obtained from sensors 210 and imaging devices 220 over a wireless communication link to other devices. This can be done continuously (e.g. for a real-time control) or only if an obstacle, incident or event is detected by one of the sensors.
    The wireless communication interfaces and wireless communication links can be implemented using known types of wireless technologies, including, but not limited to, Bluetooth, near infrared, WLAN, cellular, etc. Without limitation, the antennas can be, for example, a WLAN antenna that can be used to communicate information with a WLAN access point or an interface via a WLAN communication connection, a Bluetooth antenna, which can be used to directly communicate information to / from another Bluetooth-enabled device via a Bluetooth communication connection, and a near-infrared network antenna that can be used to directly communicate information to another device via a near-infrared communication link, a cellular antenna that can be used to communicate information to / from a cellular base station via e Cellular communication link can be used.
    A function of the wireless communication interface 240 is that it can receive an activation signal or a deactivation signal from another device and can communicate the activation signal or the deactivation signal to the processor 250 to activate or deactivate the detachable detection and warning system 100. For example, a user (e.g., a person such as a pilot, the crew, ground personnel, etc.) can use a portable computer (e.g., a smartphone) for one to enter an input or an activation command that generates an activation signal and communicates with the wireless communication interface 240 , which is then passed to processor 250 to place detachable detection and warning system 100 in a control mode.
    Processor Assembly device 202 can also use computer hardware, shown as processor 250 in Figures 3, 4, 6 and 7. Processor 250 may be communicatively coupled via a data bus to each of the blocks, as shown in FIG. 7, which is used to route signals used between processor 250 and one of the other blocks of FIG. 7. The computer hardware may also include memory as shown in FIG. 7. Memory 252 may be a non-volatile, computer readable storage medium that includes non-volatile memory (such as ROM, flash memory, etc.), volatile memory (such as RAM), or a combination of the two. The RAM stores software instructions for an operating system and software instructions that are executed by processor 250 to perform various functions described herein.
    In one embodiment, processor 250 may include a video recorder for recording images generated by imaging devices 220 and optionally an audio recorder for recording audio information recorded by microphones that may be included (not shown).
    A portion of the RAM can be used to implement temporary buffers that temporarily store images captured by imaging devices 220. As is known in the art, a "buffer" refers to a portion of physical memory that is used to temporarily store data for a time frame to determine whether that data is needed or can be discarded by another computer process. For example, the temporary buffers described here can be used to temporarily store a certain amount of image or video data. In one embodiment, processor 250, before receiving a detection signal, stores data from imaging devices 220 in non-volatile memory in a buffer-only mode so that small pieces of video information are stored (e.g., a few seconds or minutes of video) so that these small pieces can be queried if necessary. The buffer is designed to store only a limited amount of the video data preceding the event for a limited amount of time before it is discarded, unless there is a detection event so that the data is saved to a file.
    The processor 250 is configured to receive the detection signal from the detection system and to generate control signals that control the optical alarm device 280 and / or acoustic alarm device 285 of the warning system in order to cause the warning system to send one or more appropriate alarm signal (s) e) to generate.
    CH 710 961 B1
    Imaging Devices In one embodiment, mounting device 202 may also include one or more imaging devices. The imaging devices 220 that can be used may vary depending on the implementation. In general, each of the imaging devices 220 may be implemented using a video camera or other imaging device (e.g., camera). In some implementations, imaging devices 220 may be implemented using cameras such as high definition video cameras, nighttime video cameras, and / or infrared (IR) capable cameras, or any combination thereof, etc.
    The imaging devices 220 are positioned at the locations on the mounting device 202 such that when the detachable detection and warning systems 100 are attached to the aircraft 10, the imaging devices 220 are oriented so that their corresponding fields of view provide an effective field of view around the aircraft Can provide 10 of up to full three-dimensional 360 degrees. As a result, images of objects in the vicinity of the aircraft 10 can be recorded and checked. 3 and 4 include two imaging devices 220, in other implementations either fewer or more of the imaging devices may be implemented at different locations on the mounting device 202. Therefore, although the drawings show two imaging devices 220, it should be understood that the number and corresponding locations of the sensors are exemplary and not restrictive. Although the drawings show two imaging devices 220; Imaging devices are implemented by way of example and not limitation.
    [0039] Each of the imaging devices 220 can be used to acquire images of a specific area around the aircraft (including objects that are present in the vicinity of the aircraft 10). Each of the imaging devices 220 is capable of acquiring and capturing images of a particular area (within its field of view) that is near the aircraft 10 and can record images of events that occur near the aircraft. In other words, each of the imaging devices 220 is operable to acquire images of a corresponding detection zone. The images may include recognized objects, if any, and therefore the imaging devices 220 are operable to obtain an image of objects that are within a predetermined range and within a field of view associated with the imaging devices 220.
    [0040] In some embodiments, the field of view of imaging devices 220 may be invariable. In other embodiments, the field of view of imaging devices 220 is adjustable and can be varied so that the detection zone can be varied. For example, in one implementation, imaging devices 220 may be variable focal length (zoom) cameras that can be altered to change the FOV and / or viewing direction. This feature can be used to change the area and field of view based on the environment, so that the location and size of the depicted space can be changed. If the imaging devices 220 have an adjustable FOV (e.g., a variable FOV), a processor 250 may direct the camera lens to a pre-set FOV. In general, the field of view of the imaging devices 220 is typically much wider than that of the sensors 210. The range of the imaging devices 220 may also vary depending on the implementation and design of the aircraft 10.
    When processor 250 receives an activation signal, it initiates activation or release of detachable detection and warning system 100 and places it in a control mode. Processor 250 enables sensors 210 and / or imaging devices 220. In one embodiment, the imaging devices 220 are relatively weak power consumers compared to the sensors 210 and only the imaging devices 220 are enabled to observe a volume around the aircraft 10. Imaging devices 220 may have programmable threat detection and classification software that is used to identify and classify possible threats, discard those that do not require active sensors 210 (e.g., humans, animals) to be activated, and then turn on active sensors 210 if that If this is a threat, it can be used. Upon release, images from imaging devices 220 are recorded by a VCR, which may be implemented in the processor (not shown), and temporarily stored in a volatile buffer as pre-event video data. The buffer holds a limited amount of data for a limited amount of time. When the buffers fill with newer data, the older data is discarded to make room for the newer data.
    If a possible object is recognized, the system can be put into a fully active operating mode. In the active mode, imaging devices 220 are fully activated to take and record images in the volume surrounding aircraft 10. In addition, sensors 210 can also be activated. Sensors 210 perform internal processing to identify and classify possible threats. Although sensors 210 consume more power, they can also provide more accurate detection and classification. For example, a threat detection algorithm may use variables such as proximity rates and threat severity to generate detection signals that are communicated to the processor to control activation of an optical alarm device 280 and / or audible alarm device 285. The goal of the threat detection algorithm is to reduce false alarms by filtering out a non-threatening gathering activity, such as people walking past the aircraft. If one (or more) of the sensors 210 detects a triggering event (for example a movement or a movement sequence in the vicinity of the aircraft, such as an object or a person in the vicinity of the aircraft), the sensor (s) can ( en) a detection signal to processor 250
    CH 710 961 B1 communicate, which indicates that one (or more) of the sensors has detected movement near the aircraft 10. Processor 250 then creates an incident report file and stores the pre-event video data currently stored in the temporary buffers in an incident report file in memory 252 so that a record of all incidents near the aircraft can be made. Processor 250 also continues to store post-event images (provided by imaging devices 220) in the incident report file as post-event video data until a condition is met (e.g., expiration of a timer or counter), for which When the processor 250 can also generate a final incident report file and store it in the memory 252. The final incident report file may include the pre-event video data and the post-event video data that contain one or more images of an object or person approaching and / or coming into contact with the aircraft 10. The final incident report file may also contain other information such as time, date, location, information regarding triggering events and special sensors that generated the detection signals, data measured by the sensors that generated the detection signals, etc.
    In addition, if a triggering event is detected by one or more of the sensors 210 and the processor 250 receives a detection signal from one of the sensors, the processor 250 may also generate a control signal that causes an alarm signal to be generated outside of the Aircraft 10 is perceptible. For example, one of the acoustic alarm devices 285 (e.g. acoustic elements) can generate an acoustic alarm signal and / or one of the optical alarm devices 280 (e.g. lighting system) can be activated to generate an optical alarm signal. In one embodiment, imaging devices 220, sensors 210, and / or processors 250 may determine whether an incoming threat causes a warning. Different levels of warning are possible in an implementation. For example, if it is determined that a threat is occurring within a user-defined radius of the aircraft but is unlikely to come into contact with the aircraft, or if a threat that is approaching the aircraft has a relatively low proximity rate, only the visual becomes Alarm device 280 (e.g. lighting systems such as stroboscopes) activated. In contrast, if the threat is constantly approaching within a user-defined radius of the aircraft or if the threat is large and / or has a high proximity rate, a higher-level warning can be issued and both the acoustic alarm device 285 (e.g. horns, sirens , Loudspeakers etc.) as well as the optical alarm device 280 (eg lighting systems such as stroboscopes) can be activated. The alarm can continue until a condition is met (e.g. the threat withdraws from the radius defined by the user or the system detects a collision). When a collision is detected, the alarm can continue for a period of time defined by the user and then end.
    The processor 250 may also generate an incident report message and communicate the incident report message to another computer (not shown) via the wireless communication interface 240 to inform someone that an incident has occurred. The incident report message can be communicated in any known form, including, for example, email, text, or short message service (SMS), or through an automated phone call, such as a pre-recorded message. The incident report message contains information indicating that an incident occurred near that particular aircraft and may include other information such as the date and time of the incident, the location of the aircraft when the incident occurred, etc. In some embodiments, the incident report message may also include the final incident report file, while in other embodiments, it is not. The external computer can be a computer associated with the owner of the aircraft, a computer that is part of a ground support network, a server that is associated with a maintenance tracking software program, that is part of a computerized maintenance program (CMP). is a computer linked to an airport security service or law enforcement agency, etc.
    The processor 250 can also load and execute, among other things, a sensor program module, an imaging program module and an alarm generator module (from memory 252). In certain embodiments, these modules are processor-readable instructions that are stored or contained, for example, on a non-volatile processor-readable medium. Thus, references to a processor that performs functions of the present invention refer to one or more collaborative computing components that execute instructions, such as in the form of an algorithm, that are provided on a processor-readable medium, such as a memory 252, provided with a Processor 250 is linked.
    [0046] The sensor program module can be programmed to control the field of view of the sensors and to process detection signals from the sensors as soon as an object is detected by the sensors as approaching or contacting the aircraft 10. The imaging program module is programmed to control properties (e.g. the field of view) of the imaging devices and video image signals generated by the imaging devices. The imager program module also controls processing of the video image signals. In some implementations, the imager program module may be configured to process images (e.g., raw camera data) received by the imagers to determine the distance of an object from the imager, the movement of an object, etc. This data can be used by processor 250 to perform one or more tasks. The alarm generator module is designed to receive detection signals that are communicated by one of the sensors. Upon receipt of a detection signal from a particular sensor that has detected an object, processor 250 determines that an object is nearby
    CH 710 961 B1 of the aircraft 10 is located and / or contacts it, and generates an alarm generator signal that communicates it to the optical alarm device 280 and / or acoustic alarm device 285.
    Warning system In one embodiment, the warning system may include visual alarms 280 that can generate a visual indication that is perceptible outside the aircraft and provide a warning that a collision is possible and acoustic alarms 285 that generate an audible indication that is perceptible outside the aircraft and provide a warning that a collision is possible.
    Optical alarm device 280 can be any type of optical alarm device. In one embodiment, the optical alarm device 280 may include elements such as lights (e.g., LED strobe lights) that are mounted on the mounting device 202.
    The acoustic alarm device 285 can contain all known types of acoustic elements, such as loudspeakers, Homer, bells, etc., which are mounted on the mounting device 202.
    If an object (not shown) is detected by one of the sensors 210, the optical alarm device 280 and / or acoustic alarm device 285 can generate alarm signals that are perceptible outside the aircraft 10 to provide a warning that the object has been recognized ,
    [0051] Although the warning system includes two examples of an optical alarm device 280 and one example of an audible alarm device 285, in other implementations either less or more of each may be implemented in different locations on the mounting device 202.
    Power Sources Assembly assembly 202 may include power sources that provide power to the detachable detection and warning system for aircraft 10 and all of its components that use power. In one embodiment, the power source is a stand-alone power supply that does not require external connections and can supply the system maintenance-free for a long time. For example, the power source may include an energy storage device, such as a battery 260, that is configured to supply power to the detachable detection and warning system for the aircraft 10 and all of its components that use power.
    In one embodiment, the mounting device 202 may include a plurality of solar cells 204 (or photovoltaic cells) that are integrated and configured in the mounting device 202 to generate electrical energy for recharging the battery 260 (and thus power that is stored in the battery 260) to feed). The solar cells 204 can be implemented with solar modules that are integrated in the mounting device 202. Every solar cell is an electrical device that converts energy from light directly into electricity through the photovoltaic effect. This electrical energy is then stored in the battery 260.
    Those skilled in the art would also recognize that the various illustrative logic blocks, modules, and circuits described in connection with the embodiments disclosed herein may be implemented as electronic hardware, computer software, or a combination of the two. Some of the embodiments and implementations are described above in terms of functional and / or logical block components (or modules). However, it should be understood that such block components (or modules) can be implemented with any number of hardware, software and / or firmware components that are designed to perform specified functions. To clearly illustrate this interchangeability of hardware and software, various illustrative components, blocks, modules and circuits have been described above in terms of their functionality. Whether such functionality is implemented as hardware or software depends on the particular application and design restrictions that the entire system is subject to. Trained technicians can implement the functionality described in various ways for each particular application, but such implementation decisions should not be interpreted to depart from the scope of the present invention. For example, an embodiment of a system or component can include various integrated circuit components, e.g. Memory elements, digital signal processing elements, logic elements, look-up tables or the like, which can perform numerous functions under the control of one or more microprocessors or other control devices. In addition, those skilled in the art will recognize that embodiments described herein are only example implementations.
    The various illustrative logic blocks, modules, and circuits described in connection with the embodiments disclosed herein may include a general purpose processor, a digital signal processor (DSP), an application specific integrated circuit (ASIC), a field programmable gate array (FPGA) ) or other programmable logic device, separate gate or transistor logic, separate hardware components, or any combination thereof that is designed to perform the functions described herein. A general purpose processor can be a microprocessor, but alternatively the processor can be any conventional processor, controller, microcontroller, or state machine. A processor can also be implemented as a combination of computing devices, e.g. a combination of one
    CH 710 961 B1
    DSP and a microprocessor, several microprocessors, one or more microprocessors in connection with a DSP core or any other such configuration.
    The processor described here can be embodied directly in the hardware, in software modules that are executed by a processor, or in a combination of the two. A software module can be in RAM memory, flash memory, ROM memory, EPROM memory, EEPROM memory, in registers, in the hard disk, a removable disk, a CD-ROM or in any other form of storage medium, known in the art. An exemplary, non-volatile storage medium is coupled to the processor, so that the processor can read information from the storage medium and write information into it. As an alternative, the storage medium can be integrated into the processor. The processor and the storage medium can be located in an ASIC.
    [0057] The text sequence in one of the claims does not imply that procedural steps must be carried out in a chronological or logical order in accordance with this sequence, unless this is expressly defined by the claims. The method steps can be exchanged in any order without departing from the scope of the invention, as long as such an exchange does not contradict the claims and is not logically meaningless.
    Furthermore, depending on the context, words such as "connect" or "coupled to" used in describing a relationship between different elements do not imply that a direct physical connection must be made between these elements. For example, two elements may be physically, electronically, logically, or in any way connected by one or more additional elements.
    权利要求:
    Claims (10)
    [1]
    claims
    A warning, detection and anti-theft system (100) for an aircraft (10), comprising:
    A detachable mounting device (202) configured for attachment to an aircraft (10), comprising: a detection system (210) used to detect objects in the vicinity of the aircraft (10) and to generate a detection signal when an object is in the proximity of the aircraft (10) is recognized, is formed;
    a processor (250) configured to receive a detection signal from the detection system (210) and to generate control signals; and a warning system (280, 285) which, in response to at least one of the control signals, is designed to generate at least one alarm signal which is perceptible outside the aircraft (10).
    [2]
    2. The warning, detection and anti-theft system (100) according to claim 1, wherein the removable mounting device (202) further comprises:
    a belt configured to be looped around part of the aircraft (10), the belt comprising: a protective material to prevent damage to the part of the plane around which the belt is looped and a locking mechanism ( 206) which locks the belt on the aircraft to prevent the belt from being removed from the aircraft (10) until the locking mechanism (206) is unlocked;
    a battery (260) configured to supply electrical power to the warning, detection and anti-theft system (100);
    Solar cells (204) integrated and configured to generate electrical energy to provide at least a portion of the electrical power; and an imaging device (220) configured to capture and record at least one image of an object that is proximate to the aircraft (10).
    [3]
    The warning, detection and anti-theft system (100) according to claim 1, wherein the warning system comprises:
    an optical alarm device (280) which is designed to generate an optical alarm signal which is perceptible outside the aircraft (10).
    [4]
    4. The warning, detection and anti-theft system (100) according to claim 1, wherein the warning system comprises:
    an acoustic alarm device (285) which is designed to generate an acoustic alarm signal which is perceptible outside the aircraft (10).
    [5]
    5. The warning, detection and theft protection system (100) according to claim 1, wherein the detection system comprises: a sensor (210), which is designed to detect objects in the vicinity of the aircraft (10).
    [6]
    6. The warning, detection and theft protection system (100) according to claim 5, wherein the sensor (210) comprises: a proximity sensor, which is designed to detect objects in the vicinity of the aircraft (10).
    [7]
    The warning, detection and anti-theft system (100) according to claim 5, wherein the sensor comprises:
    a motion detection sensor which is designed to detect a movement of objects in the vicinity of the aircraft (10).
    [8]
    The warning, detection and anti-theft system (100) according to claim 1, wherein the detachable mounting device (202) further comprises:
    a wireless communication interface (240), which is designed to transmit and receive communication signals.
    CH 710 961 B1
    [9]
    The warning, detection and theft protection system (100) according to claim 8, wherein the wireless communication interface (240) is designed to receive an activation signal or a deactivation signal from another device, the activation signal controlling the processor (250) to activate the detachable detection and warning system and place the detachable detection and warning system in a control mode, and wherein the deactivation signal controls the processor (250) to deactivate the detachable detection and warning system.
    [10]
    The warning, detection and theft protection system (100) according to claim 1 or 8, wherein the processor (250) further comprises: a video recorder configured to record the at least one image in a temporary buffer.
    CH 710 961 B1
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    US9701424B2|2017-07-11|
    US20160288923A1|2016-10-06|
    CN106005456A|2016-10-12|
    CH710961A2|2016-10-14|
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    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    US14/674,916|US9701424B2|2015-03-31|2015-03-31|Detachable detection and warning system for an aircraft|
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