WO2013160390A2

WO2013160390A2 - Device and method for cabin pressure difference warning for an aircraft or spacecraft

Info

Publication number: WO2013160390A2
Application number: PCT/EP2013/058594
Authority: WO
Inventors: Carsten Heuer; Ilja WAIGL
Original assignee: Airbus Operations Gmbh
Priority date: 2012-04-25
Filing date: 2013-04-25
Publication date: 2013-10-31
Also published as: DE102012206877A1; WO2013160390A3

Abstract

The present invention relates to a device 10 for cabin pressure difference warning for an aircraft or spacecraft 1, comprising a cabin pressure difference sensor means 12 for detecting the current cabin pressure difference ΔΡ, a contact sensor means 16 for detecting contact by a user with an operating element 13 associated with an access element 11, an evaluation means 20, which is connected to the cabin pressure difference sensor means 12 and the contact sensor means 16 for detecting contact by the user with the operating element 13, for evaluating the data or signals which are detected by means of the cabin pressure difference sensor means 12 and by the contact sensor means 16 for detecting contact by the user with the operating element 13, and comprising a warning signal emitting means 22, which is associated with the access element 11, for emitting a cabin pressure difference warning signal to the user of the access element 11. The present invention further relates to a corresponding method for generating a cabin pressure difference warning for an aircraft or spacecraft 1 and for any corresponding aircraft or spacecraft 1.

Description

Device and method for cabin pressure difference warning for an aircraft or spacecraft

Technical field

The present invention relates to a device and a method for cabin pressure difference warning for an aircraft or space^¬ craft . Background of the invention

Although applicable to any aircraft or spacecraft, the pre^¬ sent invention and the set of problems on which it is based are described in greater detail in relation to a spacecraft for passenger transport purposes.

Aircraft which operate at high cruising altitudes are conven^¬ tionally equipped with a pressurised cabin which is accessi^¬ ble via a plurality of lockable cabin doors. The pressurised cabin ensures an internal cabin pressure which is largely in^¬ dependent of the respective altitude and the ambient atmos^¬ pheric pressure respectively prevailing there, is kept sub^¬ stantially constant, and is appropriate for the occupants of the aircraft. The internal cabin pressure is generally regu- lated via an internal pressure regulation means and what is known as a flight management system.

When the aircraft is parked on the ground again after a flight, the internal cabin pressure should correspond to the atmospheric ambient pressure again so as to ensure risk-free opening of the doors. In other words, there should not be any pressure difference between the cabin interior and the exter- nal environment. This pressure difference is also referred to in the following as the cabin pressure difference.

In particular cases, a greater or lesser cabin pressure dif- ference may occur after a flight, since the air in the air^¬ craft fuselage is heated for example by solar irradiation, and in the case of closed cabin doors and closed ventilation valves this produces overpressure in the cabin. For this reason, aircraft which have a pressurised cabin are conventionally equipped with a cabin pressure difference warning system which detects any cabin pressure difference and emits a warning signal. If modern cabin door monitoring systems detect a cabin pressure difference of more than 2.5 mbar, if in addition the escape slide of the relevant cabin door is switched off or deactivated, the cabin pressure dif^¬ ference warning is triggered. In modern aircraft, the cabin pressure difference warning is triggered in all of the cabin doors, and subsequently displayed continuously. This leads to a continuous discharge of the battery connected to the cabin pressure difference warning system. Thus, a high electrical storage capacity of the battery is required so as to ensure sufficient availability of the cabin pressure difference warning, which is associated with a high weight of the bat- tery and high technical complexity.

Against this background, an object of the present invention is to provide an improved device and an improved method for cabin pressure difference warning for an aircraft or space- craft, which extends the availability of the cabin pressure difference warning.

Disclosure of the invention This object is achieved by a device having the features of claim 1, by a method having the features of claim 9 and by an aircraft or spacecraft having the features of claim 15. Accordingly, the invention provides a device for cabin pressure difference warning for an aircraft or spacecraft. This device comprises a cabin pressure difference sensor means for detecting the current cabin pressure difference and a contact sensor means for detecting contact by a user with an operating element associated with an access element.

The device further comprises an evaluation means, which is connected to the cabin pressure difference sensor means and to the contact sensor means for detecting contact with the operating element, for evaluating the data or signals which are detected by means of the cabin pressure difference sensor means and by the contact sensor means for detecting contact by the user with the operating element.

The device further comprises a warning signal emitting means, which is associated with the access element, for emitting a cabin pressure difference warning signal to the user of the access element.

As a result of providing the contact sensor means for detect^¬ ing the contact by the user with the operating element, the cabin pressure difference pressure warning is only emitted when the operating element comes into contact with the user, and not as soon as an increased cabin pressure difference is present. The evaluation means evaluates the sensor data and triggers the cabin difference warning signal accordingly without a perceptible time delay.

It is preferably provided that the evaluation means is formed so as to actuate the warning signal emitting means to emit the cabin pressure difference warning signal in the event that the user comes into contact with the operating element and a cabin pressure difference which is greater than or equal to a predetermined threshold is detected by the cabin pressure difference sensor means. The cabin pressure differ- ence warning is thus only actuated in the event that the ac^¬ cess element is being operated. Preferably, contact itself with the operating element is sufficient for this purpose. In accordance with an advantageous development of the inven^¬ tion, it is provided that an escape slide sensor means for detecting the current state of an escape slide is provided. Thus, the current state of the escape slide can also advanta^¬ geously be taken into account in the evaluation of the sensor data.

In accordance with a further preferred embodiment, it is pro^¬ vided that the evaluation means is formed so as to actuate the warning signal emitting means for emitting the cabin pressure difference warning signal in the event that contact by a user with the operating element is detected by the con^¬ tact sensor means for detecting contact by a user with an operating element associated with an access element, where a cabin pressure difference which is greater than or equal to a predetermined threshold is detected by the cabin pressure difference sensor means, and where the escape slide sensor means for detecting the current state of the escape slide de^¬ tects that the escape slide is in a deactivated or switched- off state. The current state of the escape slide can thus al- so be taken into account in the emission of the cabin pres^¬ sure difference warning signal.

In accordance with a further preferred embodiment, it is pro^¬ vided that the contact sensor means for detecting contact by the user with the operating element is incorporated into the operating element. This advantageously reduces an assembly cost which occurs in the event of retroactive assembly, and makes reliable detection of the contact by the user with the operating element possible.

In accordance with a further preferred embodiment, it is pro^¬ vided that the evaluation means for evaluating the data de- tected by the cabin pressure difference sensor means, by the escape slide sensor means for detecting the current state of the escape slide and by the contact sensor means for detect^¬ ing contact with the operating element is integrated into the warning signal emitting means. Thus, advantageously, no addi^¬ tional constructional space has to be provided for the evalu^¬ ation means.

Preferably, it is further provided that the access element is formed by a cabin door or a freight gate. As a result, it is possible for the cabin pressure difference warning signal to be triggered by the warning signal emitting means when a cab^¬ in door or a freight gate is actuated. Preferably, in accordance with a further embodiment, it is provided that the threshold of the cabin pressure difference is approximately 2.5 mbar . As a result, advantageously, reli^¬ able opening of the access element is made possible when a cabin pressure difference below the threshold is present. Further, the cabin pressure difference warning signal is emitted when a cabin pressure difference above the threshold is present.

The invention further provides a method for generating a cab- in pressure difference warning for an aircraft or spacecraft. The method comprises detecting a cabin pressure difference by means of a cabin pressure difference sensor means and detect^¬ ing contact by a user with an operating element associated with an access element by means of a contact sensor means for detecting contact with the operating element.

The method further comprises evaluating the detected data of the cabin pressure difference sensor means and of the contact sensor means for detecting contact by the user with the oper- ating element by means of an evaluation means, which is con^¬ nected to the cabin pressure difference sensor means and the contact sensor means for detecting contact by the user with the operating element, and emitting a cabin pressure difference warning signal to the user of the access element by means of a warning signal emitting means associated with the access element.

As a result of contact by the user with the operating element being detected by means of the contact sensor means for de^¬ tecting contact with the operating element, the cabin pres^¬ sure difference warning is advantageously only emitted when the operating element is contacted by the user, and not as soon as an increased cabin pressure difference is present. The evaluation means evaluates the sensor data or sensor sig^¬ nals and triggers the cabin difference warning signal accord^¬ ingly without a perceptible time delay.

It is preferably provided that the evaluation means actuates the warning signal emitting means for emitting the cabin pressure difference warning signal in the event that contact by the user with the operating element is detected by the contact sensor means for detecting contact by a user with the operating element associated with the access element, and that a cabin pressure difference which is greater than or equal to a predetermined threshold is further detected by the cabin pressure difference sensor means.

As a result, the cabin pressure difference warning is advan^¬ tageously only activated in the event that one of the access elements is operated. Contact itself with the operating ele^¬ ment is sufficient for this purpose.

In accordance with an advantageous development of the inven^¬ tion, it is provided that the current state of an escape slide is detected by means of an escape slide sensor means for detecting the current state of the escape slide. Thus, the current state of the escape slide can also be taken into account in the evaluation of the sensor data, since when the escape slide is switched on, there is no need to emit a warn^¬ ing signal .

In accordance with a further preferred embodiment, it is pro- vided that the evaluation means actuates the warning signal emitting means for emitting the cabin pressure difference warning signal in the event that contact by the user with the operating element is detected by the contact sensor means for detecting contact by a user with an operating element associ- ated with an access element, that a cabin pressure difference which is greater than or equal to a predetermined threshold is detected by the cabin pressure difference sensor means, and that the escape slide sensor means for detecting the cur^¬ rent state of the escape slide detects that the escape slide is in a deactivated or switched-off state.

The current state of the escape slide is thus advantageously also taken into account in the emission of the cabin pressure difference warning signal.

It is preferably provided that the threshold of the cabin pressure difference is set to approximately 2.5 mbar. As a result, reliable opening of the access element is made possi^¬ ble when a cabin difference below the threshold is present. Further, a cabin pressure difference warning signal is emit^¬ ted when a cabin pressure difference above the threshold is present .

It is preferably provided that a cabin pressure difference warning signal is only emitted by the warning signal emitting means for the duration of the contact with the operating ele^¬ ment plus a follow-up period of approximately 0.5 to 30 sec^¬ onds after the operating element is released. This advanta^¬ geously extends the availability of the system, since energy or charge is only drawn from a battery belonging to the system precisely when the intention is to open the access ele^¬ ment . The present invention further relates to an aircraft or spacecraft comprising a device for cabin pressure difference warning .

Drawings

Embodiments of the invention are shown in the drawings and explained in greater detail in the following description.

In the drawings:

Fig. 1 is a schematic drawing of an aircraft or space^¬ craft comprising the device according to the invention for cabin pressure difference warning;

Fig. 2 is a schematic block diagram of a device for cab^¬ in pressure difference warning for an aircraft or space^¬ craft in accordance with a preferred embodiment; and

Fig. 3 is a flow diagram of a method for cabin pressure difference warning for an aircraft or spacecraft in ac^¬ cordance with the embodiment of Fig. 1. Description of the embodiments

Fig. 1 is a schematic drawing of an aircraft or spacecraft 1 comprising the device 10 according to the invention for cabin pressure difference warning.

The aircraft or spacecraft 1 comprises a pressurised cabin comprising a plurality of lockable access elements 11, in particular cabin doors or freight gates 11, which each comprise an operating element 13, in particular a door lever 13. Using the door lever 13, a door locking means for locking or unlocking the cabin door or the freight gate 11 can be actu^¬ ated and the cabin door or the freight gate 11 can be moved and opened or closed manually or with the assistance of an automatic door mechanism.

Alternatively, the operating element 13 may for example be formed by a handle provided on the cabin door 11.

In accordance with the present embodiment, the cabin doors 11 are each equipped with an escape slide. It must be possible to trigger the escape slide rapidly in the event of an emer- gency. To make this possible, the escape slide is first to be switched on or activated via a further actuation element. If one of the plurality of cabin doors 11 is subsequently opened, the escape slide is immediately activated and trig^¬ gered automatically by means of a triggering means. By con- trast, in normal operation (no emergency) , for example when passengers are to leave the pressurised cabin via the cabin door while the aircraft or spacecraft 1 is parked, the escape slide must not be switched on and must not be triggered. Moreover, each of the access elements 11 is formed with a warning signal emitting means 22.

An evaluation means 20 (shown in Fig. 2) is used to evaluate signals of a plurality of sensor means 12, 14, 16, in partic- ular a cabin pressure difference sensor means 12 for detect^¬ ing the current cabin pressure difference, an escape slide sensor means 14 for detecting the state of the escape slide, and a contact sensor means 16 for detecting contact by a user with a door lever 13 of one of the cabin doors 11.

In the case of a freight gate, no escape slide and thus also no emergency slide sensor means 14 for detecting the state of an emergency slide are provided. If contact by the user with the door lever 13 is detected by the contact sensor means 16 for detecting contact by the user with the door lever 13 associated with the cabin door, and if further a cabin pressure difference ΔΡ greater than or equal to 2.5 mbar is detected by the cabin pressure difference sen^¬ sor means 12, and the escape slide sensor means 14 for de^¬ tecting the current state of the escape slide detects that the escape slide is in the switched-off state, the evaluation means 20 actuates the warning signal emitting means 22 to emit a cabin pressure difference warning signal. In this con^¬ text, the aforementioned conditions preferably have to be met simultaneously .

The warning signal emitting means 22 is preferably arranged on the inside and the outside of the cabin door 11, in such a way that the cabin pressure difference warning signal is vis^¬ ible to the user both when access to and exit from the air- craft or spacecraft 1 are intended.

Fig. 2 is a schematic block diagram of the device 10 for cab^¬ in pressure difference warning for an aircraft or spacecraft 1. In the following embodiment, the device 10 is incorporated into a cabin door 11 of an aircraft or spacecraft 1. The de^¬ vice 10 for cabin pressure difference warning for an aircraft or spacecraft 1 comprises the cabin pressure difference sen^¬ sor means 12 for detecting a cabin pressure difference ΔΡ, the escape slide sensor means 14 for detecting the current state of the escape slide provided on the cabin door 11, and the contact sensor means 16 for detecting contact by the user with the door lever 13 of the cabin door 11.

The contact sensor means 16 for detecting contact by the user with the door lever 13 may for example be formed by a capaci- tive sensor or the like. Alternatively, the contact sensor means 16 for detecting contact by the user with the door lever 13 may also comprise a plurality of sensors. The device 10 for cabin pressure difference warning further comprises the evaluation means 20 for evaluating sensor data of the sensor means 12, 14, 16. The evaluation means 20 is connected to an autonomous energy supply means 18, in partic^¬ ular a battery. The evaluation means 20 is further connected to the warning signal emitting means 22 for emitting a cabin pressure difference warning.

The evaluation means 20 for evaluating the sensor data is integrated into the warning signal emitting means 22. Alterna^¬ tively, a central evaluation means 20 may also be provided for the sensor means 12, 14, 16 of the plurality of cabin doors 11.

The cabin pressure difference sensor means 12 for detecting a cabin pressure difference ΔΡ is preferably arranged in a suitable location in the interior of the pressurised cabin. In this context, the cabin pressure difference sensor means

12 is preferably connected to all of the evaluation means 20. The energy supply means 18 is provided centrally and is con^¬ nected to all of the sensor means 12, 14, 16, evaluation means 20 and warning signal emitting means 22 of a plurality of cabin doors. The escape slide sensor means 14 for detect^¬ ing the current state of an escape slide and the contact sen^¬ sor means 16 for detecting contact by a user with a door lever 13 of one of the cabin doors 11 are provided in each cabin door 11.

However, for simplicity, Fig. 2 merely shows the device 10 for cabin pressure difference warning using the example of a single cabin door 11. The warning signal emitting means 22 is provided on the cabin door 11. The warning signal may be emitted for example acous^¬ tically, optically or haptically by the warning signal emit^¬ ting means 22. The sensor means 12, 14, 16 are connected to the evaluation means 20 for evaluating the sensor data or sensor signals. The evaluation means 20 is formed to actuate the warning sig- nal emitting means 22, when predetermined conditions concern^¬ ing the sensor data are met, in such a way that it emits a cabin pressure difference warning. In particular, the evaluation means 20 actuates the warning signal emitting means 22 to emit a cabin pressure difference warning signal if the user comes into contact with the door lever 13, if a cabin pressure difference ΔΡ greater than or equal to 2.5 mbar is detected by the cabin pressure differ- ence sensor means 12, and if the escape slide is in a

switched-off state. In this context, the aforementioned con^¬ ditions preferably all have to be met simultaneously.

Fig. 3 is a flow chart of the method for cabin pressure dif- ference warning for an aircraft or spacecraft 1. The method shows the operation of the device 10 for cabin pressure dif^¬ ference warning by way of a pressure difference warning rou^¬ tine which runs in the evaluation means 20 when the aircraft or spacecraft 1 is parked on the ground and the intention is for example to open a cabin door 11 of the pressurised cabin.

Proceeding from a start function SO, in a first step SI the pressure difference ΔΡ is detected by the cabin pressure dif^¬ ference sensor means 12 and compared with a pre-set pressure difference threshold ΔΡ₃. If the detected pressure difference ΔΡ is greater than or equal to the pressure difference threshold ΔΡ₃, the pressure difference warning routine con^¬ tinues to step S2. In step S2, the escape slide sensor means 14 for detecting the state of the escape slide checks whether the escape slide is switched off or deactivated. If this is not the case, the difference pressure warning routine is left and the user is made aware, in a subroutine (not shown in Fig. 3), that the escape slide of the relevant cabin door 11 is still switched on and the escape slide first has to be de- activated. By contrast, if the emergency slide is switched off or deactivated, the difference warning routine continues to step S3. S2 is advantageously provided as an optional step. Alterna^¬ tively, the state of the escape slide may also be monitored by a different device, in such a way that step S2 can be omitted.

In step S3, the contact sensor means 16 for detecting contact by the user with the door lever 13 of the cabin door 11 checks whether the door lever 13 of the cabin door 11 is be- ing contacted or not. If this is not the case, the difference pressure warning routine is left again. By contrast if the door lever 13 is being contacted, the evaluation means 20 ac^¬ tivates the warning signal emitting means 2 and emits a pres^¬ sure difference warning signal in step S4.

The cabin pressure difference warning is preferably emitted by the warning signal emitting means 22 for between approximately 0.5 and 30 seconds for the duration of the contact with the door lever 13. In particular, it is emitted for a limited period of for example up to 10 seconds after the door lever or operating element 13 is released by the user.

The user is now advantageously informed that there is an in^¬ creased cabin pressure difference, and the pressurised cabin first has to be provided with air to balance the pressure and the ambient atmosphere before the cabin door 11 is opened .

The invention is not limited to the above embodiment. Rather, within the scope of protection, the device according to the invention or the method according to the invention for cabin pressure difference warning for an aircraft or spacecraft 1 may also take on a configuration other than the one specifi^¬ cally described above.

The device and the method for cabin pressure difference warn^¬ ing may in principle also be used in other types of vehicles or means, which have a pressurised cabin which can be sealed using a cabin door, such as submarines, space missiles, pres^¬ sure chambers, airlocks or the like.

List of reference numerals

10 Device for cabin pressure difference warning

11 Access element, cabin door, freight gate

12 Pressure difference sensor means

13 Operating means, door lever

14 Escape slide sensor means for detecting the current

state of an escape slide

16 Contact sensor means for detecting contact with an operating element of an access element

18 Energy supply means

20 Evaluation means

22 Warning signal emitting means

Claims

1. Device (10) for cabin pressure difference warning for an aircraft or spacecraft (1), comprising:

a cabin pressure difference sensor means (12) for detecting the current cabin pressure difference (ΔΡ) ;

a contact sensor means (16) for detecting contact by a user with an operating element (13) associated with an access ele^¬ ment (11) ;

an evaluation means (20), which is connected to the cabin pressure difference sensor means (12) and the contact sensor means (16) for detecting contact by the user with the operat^¬ ing element (13), for evaluating the data or signals which are detected by means of the cabin pressure difference sensor means (12) and the contact sensor means (16) for detecting contact by the user with the operating element (13); and com^¬ prising a warning signal emitting means (22), which is associated with the access element (11), for emitting a cabin pressure difference warning signal to the user of the access element (11).

2. Device (10) according to claim 1, characterised in that the evaluation means (20) is formed so as to actuate the warning signal emitting means (22) to emit the cabin pressure difference warning signal in the event that contact by the user with the operating element (13) is detected by the con^¬ tact sensor means (16) for detecting contact by the user with the operating element (13) associated with the access element (11), and that a cabin pressure difference (ΔΡ) which is greater than or equal to a predetermined threshold (ΔΡ₃) is detected by the cabin pressure difference sensor means (12) .

3. Device (10) according to either claim 1 or claim 2, characterised in that an escape slide sensor means (14) for detecting the current state of an escape slide is provided.

4. Device (10) according to claim 3, characterised in that the evaluation means (20) is formed so as to actuate the warning signal emitting means (22) for emitting the cabin pressure difference warning signal in the event that contact by the user with the operating element (13) is detected by the contact sensor means (16) for detecting contact by a user with an operating element (13) associated with an access ele^¬ ment (11), where a cabin pressure difference (ΔΡ) which is greater than or equal to a predetermined threshold (ΔΡ₃) is detected by the cabin pressure difference sensor means (12), and where the escape slide sensor means (14) for detecting the current state of the escape slide further detects that the escape slide is in a switched-off state.

5. Device (10) according to any one of the preceding claims, characterised in that the contact sensor means (16) for detecting contact by the user with the operating element (13) is incorporated into the operating element (13) .

6. Device (10) according to any one of the preceding claims, characterised in that the evaluation means (20) for evaluating the data detected by the cabin pressure difference sensor means (12), by the escape slide sensor means (14) for detecting the current state of the escape slide and by the contact sensor means (16) for detecting contact by the user with the operating element (13) is integrated into the warn^¬ ing signal emitting means (22) .

7. Device (10) according to any one of the preceding claims, characterised in that the access element (11) is formed by a cabin door or a freight gate.

8. Device (10) according to any one of the preceding claims, characterised in that the threshold (ΔΡ₃) of the cab- in pressure difference (ΔΡ) is approximately 2.5 mbar .

9. Method for cabin pressure difference warning for an air^¬ craft or spacecraft (1), comprising the following method steps :

detecting (SI) the current cabin pressure difference (ΔΡ) by means of a cabin pressure difference sensor means (12);

detecting (S3) contact by a user with an operating element (13) associated with an access element (11) by means of a contact sensor means (16) for detecting contact with the op^¬ erating element (13);

evaluating the detected data of the cabin pressure difference sensor means (12) and the contact sensor means (16) for de^¬ tecting contact by the user with the operating element (13) by means of an evaluation means (20), which is connected to the cabin pressure difference sensor means (12) and the con- tact sensor means (16) for detecting contact with the operat^¬ ing element (13); and

emitting (S4) a cabin pressure difference warning signal to the user of the access element (11) by means of a warning signal emitting means (22) associated with the access element (11) .

10. Method according to claim 9, characterised in that the evaluation means (20) actuates the warning signal emitting means (22) for emitting the cabin pressure difference warning signal in the event that contact by the user with the operat^¬ ing element (13) is detected by the contact sensor means (16) for detecting contact by a user with the operating element (13) associated with the access element (11), and where a cabin pressure difference (ΔΡ) which is greater than or equal to a predetermined threshold (ΔΡ₃) is detected by the cabin pressure difference sensor means (12).

11. Method according to either claim 9 or claim 10, characterised in that the current state of an escape slide is de- tected by means of an escape slide sensor means (14) for de^¬ tecting the current state of the escape slide.

12. Method according to claim 11, characterised in that the evaluation means (20) actuates the warning signal emitting means (22) for emitting the cabin pressure difference warning signal in the event that contact by the user with the operat- ing element (13) is detected by the contact sensor means (16) for detecting contact by a user with an operating element (13) associated with an access element (11), that a cabin pressure difference (ΔΡ) which is greater than or equal to a predetermined threshold (ΔΡ₃) is detected by the cabin pres- sure difference sensor means (12), and that the escape slide sensor means (14) for detecting the current state of the es^¬ cape slide further detects that the escape slide is in a de^¬ activated or switched-off state.

13. Method according to any one of claims 9 to 12, charac^¬ terised in that the threshold (ΔΡ₃) of the cabin pressure difference (ΔΡ) is set to approximately 2.5 mbar .

14. Method according to any one of claims 9 to 13, charac- terised in that a cabin pressure difference warning signal

(22) is only emitted by the warning signal emitting means for the duration of the contact with the operating element (13) plus a follow-up period of between approximately 0.5 and 30 seconds after the operating element (13) is released.

15. Aircraft or spacecraft (1) comprising a device (10) for cabin pressure difference warning according to any one of claims 1 to 8.