AIRCRAFT COMPRISING AT LEAST ONE EMERGENCY BEACON, AND SUCH AN EMERGENCY BEACON

Abstract

An aircraft including a fuselage having an outer face on which is fixed a second interface, at least one emergency beacon including a base having a first interface to cooperate with the second interface for fixing of the base onto the outer face, and a casing housing a control unit, a radio transmitter for transmitting a distress radio signal and detector to detect abnormal aircraft behavior, and fixing structure to take up a fixation position to ensure fixing of the casing onto the base or a separation position, in which it does not ensure fixing of the casing onto the base, the transition from the fixation position to the separation position being ordered by the control unit when the detector detect an abnormal behavior.

Description

CROSS-REFERENCE TO RELATED APPLICATION

This U.S. patent application claims priority to and the benefit of French patent application No. 14 58590 filed on Sep. 12, 2014, the entire disclosure of which is incorporated herein by reference.

BACKGROUND

The present disclosure relates to an aircraft comprising at least one emergency beacon, and such an emergency beacon.

Each aircraft is currently equipped with a radio beacon which transmits a distress signal when a problem occurs on the aircraft. Such a radio beacon is designed to transmit a signal that can be picked up by the emergency services all around the world. Such a radio beacon is installed in the fuselage of the aircraft and transmits its signal via an antenna. In a distress landing or when the aircraft is submerged, the antenna and the radio beacon may suffer damage which renders them inoperative.

Another solution, described in the patent FR-A-2 968 276, consists of a radio beacon which is ejected through the fuselage by piercing through it when an incident is detected. The radio beacon is then outside the aircraft and, in the case of submersion, it returns to the surface to transmit a more easily locatable distress signal.

Now, it is possible for a false alarm to trigger the radio beacon, which results in the piercing of the fuselage and then necessitates expensive repairs.

One object of the present disclosure is to propose an aircraft comprising an emergency beacon which does not present the drawbacks of the prior art, and in particular in which the emergency beacon is designed to not result in destruction of the structure of the aircraft when it is triggered and in which its installation does not necessitate any modification of the structure of the aircraft.

To this end, an aircraft is proposed that comprises:

• • a fuselage having an outer face on which is fixed a second interface,
  • at least one emergency beacon comprising:
    • a base having a first interface designed to cooperate with the second interface in order to ensure the fixing of the base onto the outer face, and
    • a casing in which are housed at least the following electronic components: a control unit, a radio transmitter suitable for transmitting a distress radio signal and detector designed to detect an abnormal behavior of the aircraft, and
  • fixing structure designed to take up a fixation position in which the fixing structure ensures the fixing of the casing onto the base or a separation position, in which the fixing structure does not ensure the fixing of the casing onto the base, the transition from the fixation position to the separation position being ordered by the control unit when the detector detects an abnormal behavior, and
  • in which the second interface is a physical interface designed to receive a navigation lamp, in which the first interface is a physical interface similar to that of the navigation lamp and in which the base comprises a mounting interface designed to receive a navigation lamp.

Such an emergency beacon is therefore ejected from the aircraft from its outer location when an incident is detected and the structure of the aircraft is then not damaged even in the case of a false alarm and its positioning in place of a navigation lamp avoids modifying the structure of the aircraft.

Advantageously, the casing comprises an electrical energy source.

Advantageously, the casing is equipped with an inflatable cushion designed to inflate around the casing.

Advantageously, the casing comprises a parachute designed to be deployed under the control of the control unit after the separation.

Advantageously, the aircraft comprises an electrical network designed to power the electronic components from an energy source located in the aircraft.

Advantageously, the or at least one of the emergency beacons is arranged at the rear of the fuselage.

Advantageously, the control unit comprises a memory area in which is stored a map of the Earth and a database which lists the safety threshold values linked to parameters of the aircraft and that are based on the mapping, the control unit comprises data processing software suitable for comparing the data transmitted by the detector to the database data, and for triggering the fixing structure based on these comparisons.

Advantageously, the control unit comprises a first subunit and a second subunit, each subunit comprises:

• • a first module designed and configured to deliver a first electrical signal to the fixing structure through a first wired connection; and
  • a second module designed to deliver a second electrical signal to the fixing structure through a second wired connection; and
  • for each module, a detector is provided and connected to the module and that is different from those of the other modules.

The disclosure herein also provides an emergency beacon for an aircraft according to one of the preceding variants.

BRIEF DESCRIPTION OF THE DRAWINGS

The features of the disclosure herein mentioned above, and others, will become more clearly apparent on reading the following description of an exemplary embodiment, the description being given in relation to the attached drawings, in which:

FIG. 1 represents a side view of an aircraft according to the disclosure herein;

FIG. 2 is an enlargement of the rear of the fuselage of the aircraft of FIG. 1 at its tail unit;

FIG. 3 is a schematic diagram of an emergency beacon according to the disclosure herein; and

FIG. 4 shows a particular embodiment of a control unit for an emergency beacon according to the disclosure herein.

DETAILED DESCRIPTION

FIG. 1 shows an aircraft 10 comprising a fuselage 100 having a longitudinal axis denoted X, an axis extending horizontally and laterally and denoted Y and an axis extending vertically and denoted Z. The longitudinal axis X is oriented in the direction of advance of the aircraft 10.

At the rear, the fuselage 100 has a cone 102 where an auxiliary power unit is generally arranged.

FIG. 2 shows the cone 102 to the rear of which is fixed an emergency beacon 200 according to the disclosure herein. In the rest of the description, only a single emergency beacon 200 is mentioned, but there could be several thereof distributed at different points of the fuselage 100 and therefore, more generally, at least one.

FIG. 3 shows an example of the emergency beacon 200 which is here dissociated from the fuselage 100. The emergency beacon 200 comprises a base 302 which is fixed against an outer face of the fuselage 100.

The emergency beacon 200 also comprises a casing 304 in which are housed various electronic components necessary for its operation. In particular, the casing 304 houses at least the following electronic components: a control unit, a radio transmitter suitable for transmitting a distress radio signal and a detector designed and configured to detect an abnormal behavior of the aircraft 10.

The detector embedded in the emergency beacon 200 makes the emergency beacon 200 independent of the actions of the personnel onboard the aircraft 10.

The casing 304 is fixed onto the base 302 via fixing structure 306 designed to take up a fixation position or a separation position. In the fixation position, the fixing structure 306 ensures the fixing of the casing 304 onto the base 302 and in the separation position, the fixing structure 306 does not ensure the fixing of the casing 304 onto the base 302 and the casing 304 is then released from the base 302. The casing 304 is thus mounted removably on the base 302.

To protect the electronic components that it contains, the casing 304 is preferably water-tight and dust-tight and protect these electronic components in particular from heat and impacts.

As a variant, the casing 304 can comprise thermal protection in the form of a coating of a thermally insulating material such as plastic or rubber.

The transition from the fixation position to the separation position is triggered by an order from the control unit when the detector detects an abnormal behavior of the aircraft 10.

Thus, in normal operation, the fixing structure 306 remains in fixation position and the casing 304 then remains secured to the base 302 and the outside of the fuselage 100. In emergency operation, when the detectors detect an anomaly, they inform the control unit thereof which orders the transition of the fixing structure 306 to separation position and the casing 304 is then released from the base 302 and separates from the fuselage 100.

The fixing of the base 302 onto the fuselage 100 is performed using suitable interfaces. Thus, the base 302 has a first interface 308 and a second interface 202 and is fixed onto the fuselage 100. The two interfaces 202 and 308 are designed to cooperate in order to ensure the fixing of the base 302 onto the outer face of the fuselage 100.

The second interface 202 takes the form of a physical interface designed to receive a navigation lamp, and the first interface 308 then takes the form of a physical interface similar to that of the navigation lamp and which is designed to cooperate with the physical interface of the second interface 202. Thus, it is easy to fit the emergency beacon 200 in place of an existing navigation lamp.

To ensure the fitting of the navigation lamp which is then replaced by the emergency beacon 200, the base 302 has a mounting interface 310 designed to receive the navigation lamp.

It is thus possible to equip the already existing aircraft 10 without it being necessary to modify them and, inasmuch as the emergency beacon 200, and especially the casing 304, are arranged outside the fuselage 100, the separation of the casing 304 from the aircraft 10 does not result in any damage to the fuselage 100.

Once separated, the casing 304 can transmit a distress radio signal by virtue of the radio transmitter controlled by the control unit.

To ensure a certain power reserve for the casing 304 when it is detached or enable it to operate on the aircraft 10 when no other energy source external to the casing 304 is powering it, it incorporates an electrical energy source, such as a battery.

The fixing structure 306 in one aspect is pyrotechnic or chemical, such as for example of explosive bolt type, the exploding of which is ordered by the control unit.

According to a preferred embodiment, the control unit comprises a memory area in which is stored a map of the Earth, the flight plan, and a processor containing at least one data processing software package.

The memory area also stores a database associated with the mapping which lists safety threshold values linked to parameters of the aircraft 10 and that are based on the map such as, for example, the overflight altitude, the speed, the acceleration, the altitude variation, etc., as a function of the position (longitude, latitude) of the aircraft 10.

The data processing software is suitable for comparing the data transmitted by the detector to the database data, and for triggering the fixing structure 306 based on these comparisons.

One of the software packages can be recording software designed to regularly record the data transmitted by the detector in the memory area in order to retrace a history of the flight.

The detector comprises, for example, a GPS sensor which, together with the mapping of the Earth and/or the flight plan, can detect the position and the altitude of the aircraft 10 and deduce therefrom an unsuitable position by comparison with the safety threshold values. For example, the aircraft 10 may be detected, outside of the airport areas, as being too close to the ground or the water and the control unit can then decide to trigger the emergency beacon 200.

The detector comprises, for example, one or more accelerometers which can compute an orientation of the aircraft 10 and, when this orientation does not conform to the safety threshold values of a normal flight and risks causing the aircraft 10 to crash, the control unit can decide to trigger the emergency beacon 200.

Such detector can for example assess the altitude and the angle of descent of the aircraft 10 and, if such variables do not conform to those of the flight plan, the control unit can decide to trigger the emergency beacon 200.

Such detector can for example assess the speed of approach of the aircraft 10 toward the ground, and, if this speed is higher that it should be and the aircraft 10 risks crashing, the control unit can decide to trigger the emergency beacon 200.

Such detector can, for example, detect that the aircraft has suffered an impact and the control can then decide to trigger the emergency beacon 200.

To damp the impact on the casing 304 when it reaches the ground or the water, the casing 304 is equipped with an inflatable cushion which is designed to inflate around the casing 304 under the control of the control unit immediately after its detachment from the base 302. The cushion is, for example, of the type of cushion with inflation by explosive chemical reaction. When the cushion is inflated, it completely contains all of the casing 304 and then for example takes the form of a sphere.

Such an inflatable cushion also keep the casing 304 afloat.

To avoid having the electrical energy source embedded in the casing 304 discharge, the aircraft 10 comprises an electrical network designed to power the electronic components housed in the casing 304 from an energy source located in the aircraft 10. The electrical network comprises electrical connectors and conductors inserted in the aircraft 10 and in the base 302 in order to allow for the electrical powering of the electronic components of the emergency beacon 200 and possibly of the navigation lamp from the aircraft 10.

In particular, electrical connectors are incorporated in the first interface 308, in the second interface 202, and in the mounting interface 310, and the network of conductors appropriately links the different electrical connectors.

The transmission of the distress radio signal makes it possible, by triangulation, to know the position of the casing 304 and therefore approximately that of the aircraft 10.

When the emergency beacon 200 comprises structure or one or more devices making it possible to know the geographic position of the casing 304, the distress radio signal can transmit this position.

Based on the detector contained in the casing 304, the distress radio signal can transmit flight data prior to the jettisoning of the casing 304, such as, for example, the acceleration, the position, the speed of the aircraft 10.

To recharge the electrical energy source, the casing 304 can comprise a recharging system intended to recharge the electrical energy source from the outside environment. The recharging system can comprise, for example, photovoltaic panels, or a system specifically for harvesting the energy of the waves and transforming it into electrical energy

The casing 304 can comprise a wired or wireless connection interface, making it possible to update the software implemented in particular in the control unit, and the mapping.

To slow down the descent of the casing 304 and reduce the force of the impact with the terrain (ground or water) when it is detached from the aircraft 10, the casing 304 can comprise a parachute designed to be deployed under the control of the control unit after the transition to separation position.

At least one of the beacons 200 is advantageously arranged at the rear of the fuselage 10, particularly in the embodiment of the disclosure herein described here, at the rear of the cone 102. Thus, when the casing 304 separates from the base 302, the casing 304 would not be damaged by the rest of the aircraft 10 which continues to move forward.

In the event of an incident on one of the beacons 200, a signal identical to the signal corresponding to a fault of the navigation lamp that the beacon replaces is sent to a monitoring system of the aircraft.

FIG. 4 shows a control unit 400 which comprises a first subunit 402 and a second subunit 404.

The fixing structure 306 is triggered and switched to the separation position when they receive the first electrical signal and the second electrical signal. Such an arrangement avoids having the fixing structure 306 be triggered at the command of a single electrical signal which may be a source of untimely triggering.

The first electrical signal is, for example, a +5VDC signal and the second electrical signal is, for example, a ground signal.

According to a particular embodiment of the disclosure herein, for each module 406a-b, 408a-b, a detector is provided. These detectors are connected to the module 406a-b, 408a-b and are different from the detectors of the other modules 406a-b, 408a-b in order to ensure information redundancy.

Such an arrangement mitigates a failure of at least two modules 406a-b, 408a-b of different types or of their associated detector and allow for a triggering of the fixing structure 306.

In effect, if one of the first modules 406a-b or one of the associated detector fails, the other first module 406b-a can deliver the first signal to the fixing structure 306 when the associated detector detect an abnormal behavior. Similarly, if one of the second modules 408a-b or one of the associated detector fails, the other second module 408b-a can deliver the second signal to the fixing structure 306 when the associated detector detects an abnormal behavior.

In such conditions, the fixing structure 306 will receive at least one first signal and at least one second signal and will be triggered.

The subject matter disclosed herein can be implemented at least partially in software in combination with hardware and/or firmware. For example, the subject matter described herein can be implemented in software executed by a processor or processing unit. In one exemplary implementation, the subject matter described herein can be implemented using a computer readable medium having stored thereon computer executable instructions that when executed by a processor of a computer control the computer to perform steps. Exemplary computer readable mediums suitable for implementing the subject matter described herein include non-transitory devices, such as disk memory devices, chip memory devices, programmable logic devices, and application specific integrated circuits. In addition, a computer readable medium that implements the subject matter described herein can be located on a single device or computing platform or can be distributed across multiple devices or computing platforms.

While at least one exemplary embodiment of the invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.

Claims

1. An aircraft comprising: a fuselage having an outer face on which is fixed a second interface;at least one emergency beacon comprising: a base having a first interface designed to cooperate with the second interface in order to ensure fixing of the base onto the outer face, anda casing in which is housed at least electronic components including a control unit, a radio transmitter suitable for transmitting a distress radio signal and detector designed to detect an abnormal behavior of the aircraft; andfixing structure configured to take up a fixation position in which the fixing structure ensures the fixing of the casing onto the base or a separation position, in which the fixing structure does not ensure fixing of the casing onto the base, the transition from the fixation position to the separation position being ordered by the control unit when the detector detects an abnormal behavior, andin which the second interface is a physical interface designed to receive a navigation lamp, in which the first interface is a physical interface similar to the interface of the navigation lamp and in which the base comprises a mounting interface configured to receive a navigation lamp.

2. The aircraft according to claim 1, wherein the casing comprises an electrical energy source.

3. The aircraft according to claim 1, wherein the casing is equipped with an inflatable cushion designed to inflate around the casing.

4. The aircraft according to claim 1, wherein the casing comprises a parachute designed to be deployed under control of the control unit after triggering the fixing structure from fixation position to separation position.

5. The aircraft according to claim 1, comprising an electrical network configured to power the electronic components from an energy source located in the aircraft.

6. The aircraft according to claim 1, wherein the at least one emergency beacons is arranged at a rear of the fuselage.

7. The aircraft according to claim 1, wherein the control unit comprises a memory area in which is stored a mapping of Earth and a database which lists safety threshold values linked to parameters of the aircraft and that are based on the mapping the control unit comprising data processing software suitable for comparing the data transmitted by the detector to the database data, and for triggering the fixing structure based on these comparisons.

8. The aircraft according to claim 1, wherein the control unit comprises a first subunit and a second subunit, each subunit comprising: a first module configured to deliver a first electrical signal to the fixing structure through a first wired connection; anda second module configured to deliver a second electrical signal to the fixing structure through a second wired connection; andwherein, for each module, a detector is provided that is connected to the module and that is different from a detector of other modules.

9. An emergency beacon for an aircraft according to claim 1.