Retrofittable display device for showing the activation status of an emergency slide in an aircraft, procedure and aircraft

Abstract

Display device (2) for displaying an activation status of an emergency slide in an aircraft, comprising - an optical display device (10) for emitting an optical signal, - an acoustic signaling device (12) for emitting an acoustic signal, - a sensor (14) for detecting a person's (54) approaching the display device (2); - a housing (4) with a mounting area (6) and a visible side (8); and - an electronic unit (16) coupled to the optical display device (10), the acoustic signaling device (12) and the sensor (14) and configured to operate at least one of the optical display device (10) and the acoustic signaling device (12) when the person (54) approaches at least a predetermined limit distance (32, 34), wherein the optical display device (10), the acoustic signaling device (12), the sensor (14) and the electronic unit (16) are arranged in the housing (4) to form a coherent, compact assembly which can be integrated into a door panel (26) of an aircraft door (24); wherein the fastening area (6) is designed to form a mechanical connection with a corresponding opening in the door panel (26) or a fastening means on the aircraft door (24); wherein the visible side (8) of the housing (4) faces the interior of an aircraft fuselage; and wherein the electronic unit (16) is configured to operate the optical display device (10) when the person (54) approaches below a first limit distance (32) and the acoustic signaling device (12) when the person (54) approaches below a second limit distance (34), where the first boundary distance (32) is greater than the second boundary distance (34).

Description

TECHNICAL AREA

[0001] The invention relates to a display device for indicating the activation status of an emergency slide in an aircraft, a method for indicating the activation status of an emergency slide, an aircraft with at least one emergency slide, and a display device for indicating the activation status of the at least one emergency slide. BACKGROUND OF THE INVENTION

[0002] In larger passenger aircraft, the doors can be linked to an emergency slide release mechanism, so that opening the door triggers the deployment of the attached emergency slide. Before takeoff, with the doors closed, an emergency slide release lever is moved to an "armed" position. After a normal landing, the emergency slide release lever is moved to a "disarmed" position, thus disengaging the emergency slide release mechanism and allowing the doors to be opened normally.

[0003] The position of the emergency slide release lever is clearly visible. Additionally, a warning light may be installed in or on the aircraft door, providing a visual indication of the emergency slide activation status. Nevertheless, due to time constraints and unforeseen situations on board the aircraft, it can occasionally happen that after landing, the emergency slide activation lever is left in the "armed" position, and an emergency slide is accidentally deployed when an aircraft door is opened. This can lead to damage near the aircraft and significant consequential costs due to the necessary reinstallation of the emergency slide. This is independent of the door design and the aircraft manufacturer.

[0004] Solutions exist to prevent the unintentional deployment of emergency slides, for example, through devices that detect a person approaching an aircraft door and issue a visual and / or audible warning when a person approaches the door or touches the handle, provided the emergency slide deployment system is linked to the aircraft. Such a solution may require a modification of the aircraft door.

[0005] US 2011 / 0139934A1 describes a system and method for preventing the unintentional deployment of an emergency slide for an aircraft, comprising at least one sensor for detecting the proximity of a person in front of an aircraft door and at least one optical warning device that provides a visual indication near an emergency slide release lever when the sensor detects the proximity of a person in front of the aircraft door.

[0006] DE 10 2004 048 217 A1 describes an aircraft with a cabin differential pressure warning system. The system comprises a pressurized cabin with a lockable door, an electrical power supply network, and a cabin differential pressure warning system with an autonomous warning system power supply unit independent of the electrical power supply network.

[0007] DE 10 2011 086 454 A1 describes a monitoring device for monitoring a user's movement profile in the area of ​​an actuating element of an aircraft or spacecraft, comprising at least one motion sensor designed to detect a first monitoring area of ​​the device and simultaneously a second monitoring area of ​​the device that is distinct from the first. The present invention further provides a method for monitoring a user's movement profile in the area of ​​an actuating element of an aircraft or spacecraft, comprising the following steps: detecting a first monitoring area of ​​the device using at least one motion sensor; and simultaneously detecting a second monitoring area that is distinct from the first using the at least one motion sensor.

[0008] US 2008 / 0284619A1 describes an alarm system for an aircraft door, comprising: a sensor for detecting when the door operating handle is about to be grasped by an operator, an audible alarm connected to the sensor that sounds when the sensor detects that the handle is about to be grasped, and means for activating the sensor and / or the audible alarm when the aircraft door is activated.

[0009] DE 199 09 953 A1 describes a safety and monitoring device for an emergency exit door. An electrical control unit with a microprocessor, an LED status indicator, and an electrical alarm indicator with flashing alarm light and alarm sirens are arranged in a door terminal. SUMMARY OF THE INVENTION

[0010] The object of the invention is to propose an effective device for indicating the activation status of an emergency slide and for preventing its unintentional deployment, which is particularly reliable and easy to retrofit, requiring as few major modifications as possible within the aircraft in question and, in particular, within a door.

[0011] This problem is solved by a display device having the features of independent claim 1. Further developments and advantageous embodiments can be found in the dependent claims and the following description.

[0012] A display device for indicating the activation status of an emergency slide in an aircraft is proposed. This device comprises an optical display for emitting a visual signal, an acoustic signaling device, a sensor for detecting a person's approach to the display, and an electronic unit coupled to the optical display, acoustic signaling device, and sensor. The electronic unit is configured to activate at least one of the optical and one of the acoustic signaling devices when a person approaches within a predetermined minimum distance. The optical display, acoustic signaling device, sensor, and electronic unit form a cohesive, compact assembly that can be integrated into an aircraft door panel.

[0013] The optical indicator device serves to generate a visually perceptible signal indicating to a person that an emergency slide will be deployed when an aircraft door is opened. Any indicator device can be used to generate this signal, particularly one that selectively generates a light signal, for example, a light source based on an incandescent bulb, an LED, or multiple bulbs. The light source can be configured to emit a continuous light or a flashing light, with the visual perceptibility of a flashing light potentially exceeding that of a continuous light.

[0014] Similarly, the acoustic signaling device may include a sound generation unit with which an acoustically perceptible signal can be produced. For this purpose, the sound generation unit may include an electromagnetically or piezoelectrically operated loudspeaker or buzzer and, if required or desired, a device for selectively emitting a signal sequence to reproduce a recorded or synthetic sound.

[0015] The sensor is also capable of detecting when a person approaches it and thus the display unit housing it, allowing information to be obtained as to whether and / or at what distance a person is in front of the sensor. Based on information acquired by the sensor, the associated electronic unit is able to selectively operate the visual display unit and the audible warning device. Specifically, this means that the electronic unit can emit a visual and / or audible warning signal based on a person's distance from the sensor or the display unit, alerting the person that opening the door will likely trigger the emergency slide.

[0016] By designing the display device as a compact unit that can be integrated into an aircraft door panel, a conventional warning lamp for emergency slide activation can easily be replaced by the display device according to the invention. The display device is preferably designed such that, at least in the area necessary for mounting, it resembles a conventional warning light, so that the door panel and a corresponding cutout or mounting element do not need to be modified. The display device according to the invention thus has great potential as a retrofit solution, since only a conventional warning light would need to be replaced by the display device according to the invention.

[0017] According to the invention, the display device comprises a housing with a mounting area and a viewing side. The mounting area is configured to form a mechanical connection with the door panel or a fastening element on the aircraft door. The optical display device and the sensor extend at least partially towards the viewing side. Arranging the optical display device in an area close to the viewing side allows for unobstructed perception of the optical signal generated by the optical display device. The sensor is also preferably arranged in an area close to the viewing side to enable unobstructed monitoring of a detection or monitoring area located in front of the display device and thus in front of the door panel inside the aircraft.This monitoring area is defined as a spatial section in front of the aircraft door or as a surface area of ​​the floor located in front of the door panel by selecting and fine-tuning the sensor, and extends into the aircraft interior, i.e., an area facing away from the door panel. To allow for unobstructed perception of the optical signal and uninterrupted monitoring, the sensor and the optical display device can be positioned side by side or one above the other on the viewing side.

[0018] In an advantageous embodiment, the sensor is an ultrasonic sensor. This sensor can periodically emit an acoustic signal in the ultrasonic range, which is reflected by objects located within the detection or monitoring area and returned to the sensor. The distance of the object from the sensor can be determined from the time difference between the emitted and received signal. Such sensors are technically mature, commercially available, and cost-effective. Furthermore, ultrasonic sensors are comparatively lightweight, yet allow for precise measurement and adjustable sensor behavior.

[0019] Preferably, the electronic unit has at least one activation signal input and is configured to activate or deactivate the operation of the optical indicator and the acoustic signaling device based on an activation signal received via the activation signal input. In this way, the electronic unit can make the operation of the optical indicator and the acoustic signaling device dependent on the aircraft's landing status and / or the position of an emergency slide activation lever located on the relevant door. This has the advantage that appropriate monitoring is only carried out when the aircraft has landed and the emergency slide activation lever is in a specific position, if there is a risk that the door will be opened without deactivating the emergency slide activation lever.During regular flight operations, however, monitoring is unnecessary, as there is no risk of a door being opened. An activation signal dependent on the aircraft's landing status can be generated by a separate device while the aircraft is on the ground and transmitted to the activation signal input. An activation signal dependent on the position of the emergency slide activation lever can be generated by another sensor located in or on the emergency slide activation lever, which monitors the lever's position and transmits a corresponding signal to the at least one activation signal input.

[0020] An activation signal, which depends on the aircraft's landing status, can be generated and transmitted by a central, existing system of the aircraft. It is advantageous to connect the display device according to the invention to this central system via a suitable bus or network, for example via an AFDX, CAN, or the like.

[0021] This requires that a suitable data line is present in the door or is subsequently integrated into it. However, a wireless connection device or a data transmission system based on the power line extending into the door could also be used.

[0022] In a further embodiment, the display device also includes an inertial measurement unit coupled to the electronic unit, with at least one inertial sensor for continuously or periodically detecting at least one directed acceleration. The electronic unit is configured to determine, based on the detected at least one directed acceleration, whether the aircraft is on the ground. An inertial sensor could detect both acceleration along one of three spatial axes and rotational acceleration about one of three spatial axes. By using at least one inertial sensor, the aircraft's movement can be tracked to determine whether the aircraft is on the ground or in flight. Various different methods can be used for this purpose.For example, by continuously tracking the aircraft's movements, a flight profile can be recorded, consisting of a climb phase, a cruise phase with one or more cruising altitudes, a descent phase, and a subsequent roll phase in which the aircraft decelerates significantly and acceleration in the vertical direction is negligible. It would also be possible to detect only a characteristic landing impact following a descent phase and / or a significant longitudinal deceleration of the aircraft. The different methods may require different configurations with varying numbers of inertial sensors; for detecting a landing impact, for instance, a single inertial sensor measuring acceleration along the aircraft's vertical axis might suffice. However, it is particularly advantageous to use commercially available and preferably standardized three- or three-axis inertial sensors.Six-axis sensors are used, capable of detecting both static positions and dynamic changes in position, and implemented, for example, with a three-axis yaw rate sensor and a three-axis accelerometer on a single chip. The determination of whether the aircraft is on the ground is therefore made by the display device according to the invention itself. Consequently, a connection to a bus or network that may not already be present in the door or door panel does not need to be retrofitted, making the display device according to the invention highly flexible and suitable for a wide variety of aircraft types and aircraft doors.

[0023] It is further advantageous to equip the display device and / or the inertial measurement unit with a device for specifying a flight direction, depending on the fuselage side of the corresponding aircraft door, i.e., on a right or left fuselage side. It is convenient to design the display device according to the invention as a consistently identical component that can be integrated into many different aircraft doors. The inertial measurement unit integrated into the display device can therefore be aligned with the flight direction in two different ways. The installation side of the display device must therefore be known in relation to the flight direction in order to reliably identify the aircraft's landing status using the signals supplied by the inertial measurement unit. In addition to the "factory setting" via appropriate firmware in the electronic unit, it may also be advantageous to use bridgeable pins, i.e.,a pin programming to be specified on the electronic unit during installation of the display device.

[0024] According to the invention, the electronic unit is further configured to activate the optical display device when a person approaches below a first limit distance and the acoustic signaling device when a person approaches below a second limit distance, wherein the first limit distance is greater than the second limit distance. When a person approaches the display device, it can, for example, first emit an optical signal so that the person is informed that the emergency slide is active even at a considerable distance, i.e., significantly more than an arm's length, preferably at most 1.1 m. If the person falls below the second limit distance, which is, for example, less than one or one and a half arm's lengths, preferably at most 0.5 m, an acoustic signal can also be emitted, explicitly informing the person that the emergency slide will be triggered when the handle is operated.

[0025] The housing of the display device according to the invention can be at least partially transparent in a section containing the optical display device. The housing shape therefore need not differ from that of a conventional warning lamp, and the components integrated therein are largely protected from external influences, while the visibility of the optical display device remains ensured.

[0026] The invention further relates to a method for indicating an activation status of an emergency slide in an aircraft, which comprises the steps of detecting a distance of a person from a display device in a door panel of an aircraft, comparing the distance with at least one limit distance, operating at least one optical display device and an acoustic signaling device as soon as the at least one limit distance is undershot.

[0027] In an advantageous embodiment, the optical display device is operated when a person approaches below a first limit distance, and the acoustic signaling device is operated when a person approaches below a second limit distance, wherein the first limit distance is greater than the second limit distance.

[0028] The electronic unit can also disable the operation of the at least one optical indicator and the acoustic signaling device as soon as no activation signal is received at at least one activation signal input. As mentioned above, this can be a signal dependent on a landing condition and / or a signal dependent on the position of an emergency slide activation lever.

[0029] Furthermore, the method allows for the continuous or periodic detection of at least one directed acceleration via an inertial measurement unit coupled to the electronic unit and arranged in the display device. This unit uses at least one inertial sensor to determine whether the aircraft is on the ground and, if so, generates an activation signal and transmits it to the electronic unit. As mentioned above, the inertial measurement unit preferably comprises a three-axis or six-axis sensor.

[0030] The invention further relates to an aircraft with at least one door and a door panel attached thereto inside the aircraft, as well as a display device with the aforementioned features on the door panel. BRIEF DESCRIPTION OF THE FIGURES

[0031] Further features, advantages, and applications of the present invention will become apparent from the following description of the exemplary embodiments and the figures. All features described and / or illustrated, individually and in any combination, constitute the subject matter of the invention, irrespective of their composition in the individual claims or their cross-references. In the figures, the same reference numerals denote identical or similar objects. Fig. Figure 1 shows a display device in a three-dimensional view. Fig. Figure 2 shows a possible installation position for the display device. Fig. Figure 3 shows the display unit in a four-view drawing. Fig. Figure 4 shows the display unit in a partially disassembled view. Fig. Figure 5 shows possible sound beams of an ultrasonic sensor. Fig. Figure 6 shows a person standing in front of an aircraft door and a triggered display. Fig. Figure 7 shows the display device in a schematic, block-based representation. DETAILED PRESENTATION OF EXEMPLARY EXECUTION FORMS

[0032] Fig. Figure 1 shows a display device 2 according to the invention, which has a housing 4 with a mounting area 6 and a viewing side 8. An optical display device 10, which by way of example has several light sources 18, is integrated into the display device 2. Fig. A concealed acoustic signaling device 12 and a sensor 14 for detecting the distance of an object from the display device 2 are arranged. By way of example, the optical display device 10 and the sensor 14 are arranged one below the other or next to each other, i.e., following one another along a spatial axis, on the visible side 8, while the acoustic signaling device 12 is positioned, by way of example, inside the display device 2, facing away from the visible side 8. The mounting area 6 can further comprise elastic retaining clips 15 which, when the mounting area 6 is inserted into a corresponding opening in a door panel, form a positive and / or force-fit connection with it.

[0033] An electronic unit 16, arranged in the display device 2, of which a circuit board is particularly visible in this illustration, is connected to the optical display device 10, the acoustic signaling device 12, and the sensor 14 and is configured to selectively operate the optical display device 10 and the acoustic signaling device 12 based on a detected distance of an object to the display device 2 or the sensor 14. This can be achieved, for example, by defining at least one in Fig. The maximum distance 32, 34 shown in Figure 2 is reached, which an object may reach at most, so that the optical display device 10 or the acoustic signaling device 12 can be operated.

[0034] The electronic unit 16 can have an activation signal input to which an activation signal can be sent. This is used to initiate the operation of the optical display device 10 and the acoustic signaling device 12 only when the aircraft is on the ground and the corresponding aircraft door can be opened at any time.

[0035] In the illustrated embodiment, the optical display device 10 is separated from the viewing side 8 only by a transparent cover 13 or arranged in a cutout therein, so that unrestricted visibility of the optical display device 10, i.e., the light sources 18, which are suitable for generating sufficiently bright light, either pulsed or continuous, is permitted. Furthermore, the optical display device 10 features, by way of example, lettering 20 ("Slide Armed"), which is designed as the only non-transparent surface of the optical display device 10. Alternatively, the lettering 20 can also be implemented as the only translucent surface of the optical display device 10.

[0036] Sensor 14 is an example of an ultrasonic sensor that periodically emits ultrasonic signals and determines the distance to the object in front of the sensor from the time difference between the emitted sound waves and the received sound reflections. Alternatively, other types of sensors can be used, such as optical, camera-based, or radar-based sensors.

[0037] The display unit 2 is designed as a very compact component that can be installed in place of a conventional warning light in a door panel or similar location. As previously mentioned, to avoid excessive triggering of visual or audible warning signals, it is advisable to operate the visual display unit 10 and / or the audible signaling unit 12 only when the aircraft is on the ground and the aircraft door is about to be opened. This can be achieved particularly easily by receiving an activation signal at the activation signal input, although this requires a data line to a central unit on board the aircraft.

[0038] In the illustrated embodiment of the display unit 2, an inertial measurement unit (IMU) 22, concealed here, is integrated. This IMU is designed to detect the spatial movements of the aircraft and transmit them to the electronic unit 16. The landing of an aircraft can be detected by distinct events, such as a landing impact after a continuous descent, whereby the detected altitude of the aircraft remains practically unchanged after the landing impact. Once this event has occurred, the electronic unit 16 can monitor the aircraft and issue corresponding visual or audible warnings.

[0039] Fig. Figure 2 shows an example of an aircraft door 24 with a door panel 26 facing the interior of the aircraft fuselage. When the aircraft is on a runway or in a parking position, the door 24 is opened from the inside of the aircraft. The display device 2 is integrated on or into the door panel 26, with the viewing side 8 facing into the interior of the aircraft.

[0040] If a person is therefore in front of door 24, they are within the detection range of sensor 14. As indicated, sensor 14 monitors a room 28 on the inside of the aircraft and defines a detection range 30 there. For example, the electronic unit 16 can define a first limit distance 32 and a second limit distance 34, wherein the electronic unit 16 operates the optical indicator 10 as soon as a person falls below the first limit distance 32 and wherein the acoustic signaling device 12 is operated as soon as a person falls below the second limit distance 34. For the first limit distance 32, it is advantageous to provide a distance of at most 1.1 m and preferably 0.9 m. For the second limit distance 34, a distance of at most 0.5 m and preferably 0.35 m is advantageous.

[0041] If a person is located between the two lines indicating the boundary distances 32 and 34, they will only be alerted visually, for example by a flashing light, to the still-activated emergency slide. If the person continues to approach door 24, an audible signal will also sound when the distance to door 24 is close to arm's length. Of course, the two boundary distances 32 and 34 can also be the same, in which case visual and audible signals will be given simultaneously.

[0042] Fig. Figure 3 shows a four-view drawing of the display device 2, in which a bottom surface 36 with an electrical connection 38 is shown, which is to be connected to a power supply of the door 24 and is further coupled to a sensor (not shown) that monitors the emergency slide activation lever 31. This can be implemented either via an activation signal that depends on the position of the emergency slide activation lever 31 or via a power supply that depends on the position of the emergency slide activation lever 31.

[0043] A narrow end 40 of the viewing area 8 mainly features the sensor 14, which is located in Fig. The installation shown in Figure 2 is directed directly into the interior of the aircraft fuselage. The lighting devices 18, which are distributed along the side wall 42 inside the cover 13, are visible on a side wall 42. The mounting area 6 is narrower than the viewing area 8, so that when the display device 2 is snapped into an opening, an edge 44 facing the mounting area 6 can rest on an edge of the opening in question, and the retaining clips 15 facilitate flush contact between the edge 44 and the edge of the opening in question.

[0044] The lettering 20 is arranged on a top surface 46 and essentially occupies the available width of the cover 13. Due to the transparency of the cover 13, further lighting devices 18 are visible, which backlight the lettering 20.

[0045] Fig. Figure 4 further shows the display device 2 in a partially disassembled arrangement, in which an inertial measurement unit 48 integrated into the electronic unit 16 is visible, which can detect the movement of the display device 2 and thus of the aircraft. By evaluating significant events, such as a landing impact and a subsequent sharp reduction in longitudinal speed due to braking, followed by a constant altitude, it can be clearly determined that the aircraft is on the ground. This event can trigger an activation signal, which initiates the activation of the monitoring of the area in front of door 24.

[0046] A diagram in Fig. Figure 5 further shows two preferred sound beams 50 and 52 of the ultrasonic sensor 14, wherein sound beam 50 belongs to an ultrasonic sensor with an aligned plate and sound beam 52 to an ultrasonic sensor with a tube having a diameter of, for example, 27 mm. For the precise detection of a person directly in front of the ultrasonic sensor approaching the door 24, the sound beam should be set as narrow as possible, achieving a width of significantly less than one meter and preferably 0.3 to 0.7 m. The detection range 28 is thus quite narrow and can ignore people further away to the side. The use of an aligned plate allows for a slightly wider sound beam 50 compared to the solution with a tube.

[0047] In Fig. Figure 6 depicts a person 54 approaching door 24, having already exceeded the first boundary distance 32 and reached the second boundary distance. Simultaneously, a visual and an audible warning are emitted, clearly warning person 54 not to open door 24 with the emergency slide activation lever 31 in an activated position.

[0048] Finally, it Fig.Figure 7 shows an embodiment of the display device 2 in a schematic, block-based representation. The ultrasonic sensor 14 and the inertial measurement unit 48 are connected to the electronic unit 16, which also has two activation signal inputs 56 and 58. The inertial measurement unit 48 can generate an activation signal via a corresponding logic circuit 60, which represents a successful landing, and in this case, the activation signal is sent to activation signal input 56. Another activation signal can be sent to the second activation signal input, which represents an activation position of an emergency slide activation lever. If the aircraft is on the ground and the emergency slide activation lever is in an activation position, monitoring of the detection area 30 is initiated.If the electronic unit 16 detects that an object is located within at least a limit distance 32, 34, an optical signal 62 and / or an acoustic signal 64 is triggered.

[0049] It is understood that filters 66 and 68 are connected downstream of the inertial measurement unit 48 and the ultrasonic sensor 14, respectively, to achieve the desired signal quality. A power supply unit 70 is also connected to terminal 8. Additionally, a pin programming unit 72 is connected to or integrated with the display unit, in particular to specify the orientation of the display unit 2 relative to the direction of flight.

[0050] It should be further noted that "have" does not exclude other elements or steps, and "a" or "an" does not exclude a plurality. It should also be noted that features described with reference to one of the above embodiments may also be used in combination with other features of other embodiments described above. Reference numerals in the claims are not to be considered as a limitation.

Claims

[1] Display device (2) for displaying an activation status of an emergency slide in an aircraft, comprising - an optical display device (10) for emitting an optical signal, - an acoustic signaling device (12) for emitting an acoustic signal, - a sensor (14) for detecting a person's (54) approaching the display device (2); - a housing (4) with a mounting area (6) and a visible side (8); and - an electronic unit (16) coupled to the optical display device (10), the acoustic signaling device (12) and the sensor (14) and configured to operate at least one of the optical display device (10) and the acoustic signaling device (12) when the person (54) approaches at least a predetermined limit distance (32, 34), wherein the optical display device (10), the acoustic signaling device (12), the sensor (14) and the electronic unit (16) are arranged in the housing (4) to form a coherent, compact assembly which can be integrated into a door panel (26) of an aircraft door (24); wherein the fastening area (6) is designed to form a mechanical connection with a corresponding opening in the door panel (26) or a fastening means on the aircraft door (24); wherein the visible side (8) of the housing (4) faces the interior of an aircraft fuselage; and wherein the electronic unit (16) is configured to operate the optical display device (10) when the person (54) approaches below a first limit distance (32) and the acoustic signaling device (12) when the person (54) approaches below a second limit distance (34), where the first boundary distance (32) is greater than the second boundary distance (34). [2] Display device (2) according to claim 1, wherein the sensor (14) is an ultrasonic sensor. [3] Display device (2) according to claim 1 or 2, wherein the electronic unit (16) has an activation signal input (56, 58) and is configured to activate or interrupt the operation of the optical display device (10) and the acoustic signaling device (12) based on an activation signal receivable via the activation signal input (56, 58). [4] Display device (2) according to claim 3, wherein the activation signal input (56, 58) is coupled to a central system of the aircraft and the activation signal is generated and transmitted by the central system of the aircraft. [5] Display device (2) according to claim 3, further comprising an inertial measuring unit (22) coupled to the electronic unit (16) with at least one inertial sensor (48) for continuously or periodically detecting at least one directed acceleration, wherein the electronic unit (16) is configured to determine, from the detected at least one directed acceleration, whether the aircraft is on the ground. [6] Method for displaying an activation status of an emergency slide in an aircraft with a display device (2) according to any one of claims 1 to 5, the method comprising the steps: - Detecting the distance of the person (54) from the display device (2) in the door panel (26) of the aircraft, - Comparing the measured distance with at least one limit distance (32, 34), - Operate at least one of the optical display device (10) and the acoustic signaling device (12) as soon as the minimum limit distance (32, 34) is undershot. [7] Method according to claim 6, wherein the optical display device (10) is operated when the person (54) approaches below a first limit distance (32) and the acoustic signaling device (12) is operated when the person (54) approaches below a second limit distance (34), where the first boundary distance (32) is greater than the second boundary distance (34). [8] Method according to claim 6 or 7, wherein the electronic unit (16) prevents the operation of the at least one optical display device (10) and the acoustic signaling device (12) as soon as no activation signal is received at an activation signal input (56, 58). [9] Method according to any one of claims 6 to 8, further comprising the steps: - continuous or periodic detection of at least one directed acceleration via an inertial measurement unit (22) coupled to the electronic unit (16) with at least one inertial sensor (48), - Determine from the recorded at least one directed acceleration whether the aircraft is on the ground and, - when the aircraft is on the ground, generating an activation signal and transmitting the activation signal to an activation signal input (56, 58) of the electronic unit (16). [10] Aircraft comprising an aircraft fuselage, at least one opening arranged therein and closable by an aircraft door (24), wherein the aircraft door (24) has a door panel (26) directed towards the interior of the aircraft fuselage and attached thereto and a display device (2) according to any one of claims 1 to 5.

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