Aircraft having a warning device

An aircraft having a warning device for generating a whistling sound has a fuselage and a warning device. The warning device has a sound-generating element which is designed to generate a whistling sound if the aircraft is in an uncontrolled dive in the direction of the surface of the earth and there is a flow of fluid against the sound-generating element. The warning device is at least partially arranged on the fuselage of the aircraft.

FIELD OF THE INVENTION

The invention relates to an aircraft. In particular, the invention relates to an aircraft having a warning device for generating a whistling sound.

BACKGROUND OF THE INVENTION

Unmanned aircraft, also referred to locally as drones, are continuously undergoing further development and are of interest for a wide variety of areas of application.

Efforts are being made, for example, to use such aircraft in logistics or in the delivery of mail. It is therefore to be expected that such aircraft will become more widespread and a large number of such aircraft will be in use in future. Since the flying routes can also run over (densely) populated areas, it is desirable to take suitable safety precautions, in order to warn people if the flying objects are damaged by internal and external influences and will fall to the ground.

BRIEF SUMMARY OF THE INVENTION

An aspect of the invention relates to making available an aircraft having a warning device which functions under virtually all operating conditions.

According to one aspect of the invention, an aircraft is disclosed which has a fuselage and a warning device. The warning device has a sound-generating element which is designed to generate a whistling sound when the aircraft is in an uncontrolled dive in the direction of the surface of the earth, and there is a flow of fluid against the sound-generating element. The warning device is arranged at least partially on the fuselage of the aircraft.

The fluid flows against the sound-generating element if the aircraft is in an uncontrolled dive. This can ensure that even in the event of a power loss an acoustic warning signal is generated as a whistling sound, in order to warn persons about the falling aircraft.

The fuselage relates to the essential structural features of the aircraft. The fuselage has, for example, a core structure, wings, drive units and an outer skin, wherein the core structure is that element to which the other parts of the fuselage are attached.

The fluid can also be referred to as air or gas.

The whistling sound relates to a sound which is generated by virtue of the fact that a flow of air is divided or deflected or diverted by a sharp edge or a similar obstacle, as a result of which eddies are produced which, through interaction with a cavity, generate a soundwave.

The cavity can also be referred to as a resonator space.

A multiplicity of sound-generating elements can be arranged at various locations on the fuselage, in particular on the outer skin of the aircraft. In this context, the sound-generating element can preferably be attached at locations on the outer skin of the aircraft in such a way that in an uncontrolled dive of the aircraft a flow of air flows against the sound-generating element.

The direction in which the oncoming flow of fluid flows relates to a direction of flow which flows basically perpendicularly onto the falling aircraft when viewed from the surface of the earth.

In the event of the aircraft falling in a dive with its nose in the direction of the surface of the earth, the longitudinal axis of the aircraft is basically perpendicular with respect to the surface of the earth. In this example, the oncoming flow of fluid flows in the direction of the longitudinal axis, with the result that the sound-generating element is arranged in such a way that the oncoming flow of fluid flows against it.

The longitudinal axis of the aircraft can also be referred to as the x direction. The transverse axis of the aircraft can also be referred to as the y direction. The vertical axis of the aircraft can also be referred to as the z direction.

In the event of the aircraft spinning, there is a non-uniform flow of the fluid against the outer skin. Therefore, in this example a plurality of sound-generating elements can be arranged in different directions along the outer skin, in order to ensure that the fluid for generating the whistling sound flows against the sound-generating element even in the case of a spinning aircraft.

The sound-generating element can therefore ensure that a whistling sound is generated by an oncoming flow. A power supply is not necessary to generate the whistling sound. As a result, the whistling sound can be output even when there is a complete power loss of the aircraft.

Furthermore, the aircraft can, however, also have further sound sources. In one example, the aircraft can have a loudspeaker which generates a warning sound. The loudspeaker can be connected to a power supply source of the aircraft. The power supply of the loudspeaker can also be embodied by means of a battery, with the result that the loudspeaker can emit a warning sound even in the event of a power loss.

According to one embodiment, the sound-generating element is a recess in the outer skin of the aircraft. The sound-generating element can as a result be designed so as to be at least partially integrated in the outer skin of the aircraft. For example, an inner wall which runs parallel to the outer wall can be arranged on the outer skin, in order to form a cavity between the outer skin and the inner wall. Alternatively, the outer skin can be of double-walled design at this point. The inner wall can be connected to the outer skin by means of connecting fins. The fluid can flow via an inlet into the cavity formed by the outer skin and the inner wall, and can flow out of an outlet again. Such an embodiment has the advantage that the aerodynamic properties of the aircraft are not adversely affected, or at most are adversely affected only to a small degree.

According to another embodiment, the sound-generating element is a projection on the outer skin of the aircraft. In one example, the sound-generating element can be mounted on the outer skin of the aircraft, for example screwed, riveted, welded or bonded, or else as a combination of a plurality of types of attachment, e.g. screwed and bonded. As a result, a simple method of manufacture and maintenance can be attained because the sound-generating element is easily mounted on the outer skin and can also be used as a retrofitting kit for existing aircraft.

According to one embodiment of the invention, the sound-generating element has an inlet and a cavity and/or an outlet. The geometric dimensions of the inlet, of the cavity and of the outlet can be embodied as a function of the desired frequency. In one example, the sound-generating element can be dimensioned in such a way that a whistling sound is generated in a frequency range which can be perceived by humans, e.g. between several hundred Hz up to 20 kHz. It is possible that the sound-generating element is merely a depression in the form of a blind hole and that the upper edges of the blind hole are shaped in such a way that a fluid which flows past the blind hole gives rise to a whistling sound. In this case, the sound-generating element does not have an outlet and there is no flow through the cavity. The fluid merely flows past an opening of the blind hole and is deflected by the edges on the opening of the blind hole in order to generate the whistling sound.

According to a further embodiment of the invention, the sound-generating element is embodied as a whistle for generating a whistling sound. In one example, the cavity of the whistle can be a tubular cavity which runs either outside the aircraft or inside the aircraft, along the outer skin. The fluid flows against the inlet of the whistle and flows out of the outlet of the whistle again via the cavity, with the result that a whistling sound is generated.

According to a further embodiment of the invention, the warning device has a blocking apparatus. As a result, it can be ensured that the whistling sound does not generate a whistling sound during the planned flight. In addition it can be ensured that the sound-generating element is not soiled and is capable of use where necessary. The blocking apparatus can also be referred to as a protection device and is, in particular, embodied in a closed or blocked state to prevent a flow of fluid getting through to the sound-generating element. The blocking apparatus can in addition also assume an opened state. In the opened state, a fluid, for example air, can get through to the sound-generating element and generate the whistling sound.

According to a further embodiment of the invention, the blocking apparatus has a shutter and a securing element, wherein the securing element is embodied in such a way that the shutter closes the sound-generating element by means of the securing element if the aircraft is in controlled flight, in order to prevent the flow of fluid from flowing against the sound-generating element in order to generate a whistling sound.

According to a further embodiment of the invention, the securing element is embodied in such a way that the shutter opens if the aircraft is in an uncontrolled dive in the direction of the surface of the earth, in order to permit the flow of fluid to flow against the sound-generating element, in order to generate a whistling sound.

According to a further embodiment of the invention, the blocking apparatus is arranged at the inlet and/or inside the cavity and/or at the outlet of the sound-generating element.

According to a further embodiment of the invention, the securing element has an elastic element, in order to secure the shutter in a closed state. The elastic element is dimensioned in such a way that the shutter opens starting from a specific pressure, wherein the specific pressure occurs in the case of an uncontrolled dive of the aircraft in the direction of the surface of the earth. In one example, the securing element yields starting from a certain air pressure, with the result that the shutter is moved from the closed state into the opened state. The specific air pressure occurs in the case of an uncontrolled dive of the aircraft in the direction of the surface of the earth. In one example, when there is a flow against the shutter starting from a certain air pressure into the cavity the shutter can fold or clear the opening in the sound-generating element and therefore allow the oncoming flow of fluid into the cavity.

In a further example, the blocking apparatus can also have an acceleration-detection unit which detects an acceleration pattern which is typical of a dive of the aircraft and is coupled to the securing element in such a way that the shutter opens.

According to a further embodiment, the securing element has a magnetic element, in order to secure the shutter in a closed state. The magnetic element is dimensioned in such a way that the shutter opens when there is a powerloss, i.e. the magnetic element is dimensioned in such a way that in the event of a powerloss the securing element no longer secures the shutter in the closed state. The magnetic element secures the shutter in the closed state as long as the magnetic element is supplied with power. In the event of a power loss or power failure, the magnetic element loses its effect and the shutter is no longer secured in the closed state and opens. As a result it is ensured that in the event of a power loss there can be a flow against the sound-generating element if the aircraft is in an uncontrolled dive.

According to a further embodiment of the invention, the blocking apparatus has a film. The film is embodied in such a way that the film tears if there is a flow with a specific air pressure against the film, wherein the specific air pressure occurs when there is an uncontrolled dive of the aircraft in the direction of the surface of the earth. The film can preferably be arranged at an inlet of the sound-generating element. This has the advantage that the film is easily accessible and can easily be replaced where necessary or can be checked for its functional capability before each flight, e.g. it can be checked for leakproofness or correct seating at the inlet of the sound-generating element.

In another example, a further blocking apparatus can also additionally be attached to the outlet of the sound-generating element. As a result, the sound-generating element can be protected against the penetration of moisture and dirt both at the inlet and at the outlet.

According to a further embodiment, in each case at least one warning device is arranged in an x direction, in a y direction and in a z direction of the aircraft. This means that the warning devices are arranged in such a way that they generate the whistling sound if the flow of air or another flow of fluid flows in the x direction, y direction or z direction. In one example, the warning device is arranged in such a way that in the case of an uncontrolled dive there is a flow of air against the warning device in every position and direction of movement. As a result, it can be ensured that the whistling sound is generated in every position and direction of movement of the aircraft in the air if the aircraft is in an uncontrolled dive. For example, if the aircraft is spinning, the warning device can be arranged on the outer skin in such a way that the whistling sound is generated by the airflow by at least one warning device in every position and direction of movement of the aircraft.

According to a further embodiment, the aircraft is an unmanned aircraft. In one example, the aircraft can be a drone with a weight of less than 25 kg.

DETAILED DESCRIPTION

The illustrations in the figures are schematic and are not true to scale.

If identical reference symbols are used in the following description of the figures, they relate to identical or similar elements.

FIG. 1shows an aircraft100having a fuselage102. The aircraft has a warning device10. The warning device10has a sound-generating element12which is designed to generate a whistling sound if the aircraft100is in an uncontrolled dive in the direction of the surface of the earth and there is a flow of fluid against the sound-generating element12. The warning device10is at least partially arranged on the fuselage102of the aircraft.

In the example shown here, the warning device10is arranged on the fuselage102. The warning device10can, however, be arranged at any desired location on an outer skin14of the aircraft. In an example which is not shown, the warning device10can be arranged on the outer skin14of the wings of the aircraft. Furthermore, a plurality of warning devices can be arranged on the outer skin14of the aircraft100. The warning devices10can be arranged in such a way that the airflow in the case of an uncontrolled dive of the aircraft can flow against at least one warning device10. For example, the warning device can be arranged in such a way that the longitudinal axis of the warning device runs along the longitudinal axis of the aircraft (x direction) on the outer skin14of the aircraft, with the result that in the case of a dive there is a flow against the warning device, in order to generate the whistling sound, if the aircraft falls nose down in the direction of the surface of the earth. As a result it is ensured that depending on the position and the direction of movement of the aircraft100in a dive there is a flow against at least one warning device10in such a way that a whistling sound is generated. The longitudinal axis of the aircraft can also be referred to as the x direction. The transverse axis of the aircraft100can also be referred to as the y direction. The vertical axis of the aircraft10can also be referred to as the z direction.

FIGS. 2aand 2bshow exemplary embodiments of the sound-generating element12of the warning device10of the aircraft100(FIG. 1), which sound-generating element12is arranged, for example, along the longitudinal axis (x direction) of the aircraft100and against which the air flow flows (shown schematically by the upwardly directed arrows) during an uncontrolled dive in the direction of the surface of the earth. In the schematic illustration inFIG. 2aandFIG. 2bthe aircraft100is falling vertically in the direction of the surface of the earth, i.e. the longitudinal axis of the aircraft100is positioned perpendicularly relative to the surface of the earth.

The sound-generating element12can be embodied, for example as a whistle for generating a whistling sound. In one example, a cavity18of the whistle can be a tubular cavity which runs along the outer skin14either outside the aircraft100or inside the aircraft100. The airflow flows into an inlet16of the sound-generating element12and flows out of an outlet20again via the cavity18, with the result that a whistling sound is generated.

In the example shown inFIG. 2a, the sound-generating element12is a recess in the outer skin14of the aircraft100(FIG. 1). As a result, the sound-generating element12can be embodied partially integrated into the outer skin14of the aircraft100. For example, a parallel inner wall can run on the outer skin, in order to form a cavity18between the outer skin14and the inner wall. In one example, reinforcement fins21(generally a carrying or supporting structure) can be arranged between the inner wall and the outer skin, in order to attach the outer skin to the inner wall. The fluid can flow via an inlet16into the cavity18formed by the outer skin14and the inner wall, and flow out via an outlet20. Such an embodiment has the advantage that the aerodynamic properties of the aircraft are not adversely affective or are at most adversely affected to a small degree. A whistling sound is generated at the sound-generating element12by the airflow. The reinforcement fins21are embodied and arranged in such a way that they do not adversely affect, or hardly adversely affect, the airflow between the inlet and outlet.

FIG. 2bshows a further example of the sound-generating element12. In the example shown here, the sound-generating element12is embodied as a projection on the outer skin of the aircraft100. In one example, the sound-generating element12can be welded or bonded to the outer skin13of the aircraft100. As a result, a simple manufacturing method and maintenance can be attained. In other words, the sound-generating element12can be a tubular structure with the cavity18, the inlet16and the outlet20, which tubular structure is attached to the outer skin14of the aircraft or integrated in the outer skin14. The inlet16is illustrated by a dashed line, in order to clarify that the inlet is opened. The dashed line merely constitutes a line of sight.

A whistling sound is generated by the flowing of a flow of air against the sound-generating element12of the aircraft100. As a result it can be ensured that in the event of a power loss the aircraft100can emit a warning signal in the case of a dive, in order to warn persons on the ground. In an example which is not shown here, further sound sources for outputting warning signals can also be arranged on the aircraft. For example, loudspeakers can be arranged on the aircraft. Said loudspeakers can be connected to a power supply source of the aircraft or can be operated by means of a separate redundant energy source (e.g. batteries). The supply of the loudspeakers via batteries has the advantage that the loudspeaker can output further warning sounds in addition to the whistling sound in the event of a power loss.

FIG. 3a,FIG. 3bandFIG. 3cshow schematic illustrations of exemplary embodiments of the warning device10. The warning device10has a blocking apparatus22. The blocking apparatus blocks the airflow through the cavity18and can be arranged either on the inlet or on the outlet or on both. As a result it can be ensured that the whistling sound does not generate a whistling sound during a planned flight, i.e. in controlled flight. In addition, it can be ensured that the sound-generating element12is not soiled and is and remains capable of use when required.

In one example, as shown, for example, inFIG. 3aandFIG. 3b, the blocking device22has a shutter24and a securing element26, wherein the securing element26is embodied in such a way that the shutter24blocks the sound-generating element12by means of the securing element26if the aircraft100is in controlled flight, in order to prevent the fluid flow from flowing against the sound-generating element12in order to generate a whistling sound. Furthermore, the securing element26is embodied in such a way that the shutter24opens the sound-generating element12by means of the securing element26if the aircraft100is in an uncontrolled dive in the direction of the surface of the earth, in order to permit the fluid flow to flow against the sound-generating element12in order to generate a whistling sound. The blocking device is therefore a purely passive element and is moved into the opened state by the fluid flow if the fluid pressure acting on the blocking apparatus exceeds a specific threshold value or if the aircraft exceeds a specific speed.

The blocking device22can be arranged on the inlet16and/or inside the cavity and/or on the outlet20of the sound-generating element20. InFIG. 3aandFIG. 3b, the blocking apparatus22is arranged at the inlet16. InFIG. 3c, the blocking apparatus22is arranged at the outlet20.

FIG. 3ashows two warning devices with a similar functional principle. On the left-hand side, a securing element26secures the shutter in the closed state. Once the shutter opens, it also remains in the opened state because the securing element no longer applies any force to the shutter after the opening. On the right-hand side, the securing element26(e.g. a compression spring) continuously applies a compressive force to the shutter and counteracts the fluid pressure. Here, the shutter can be opened by the fluid pressure and is closed again by the securing element26if the fluid pressure decreases.

In both variants inFIG. 3a, the securing element26has an elastic element27a, in order to secure the shutter24in a closed state. The elastic element27ais dimensioned in such a way that the securing element26no longer secures the shutter24in the closed state starting from a specific air pressure, wherein the specific air pressure occurs in the case of an uncontrolled dive of the aircraft100in the direction of the surface of the earth. In one example when the airflow flows against the shutter24the shutter24can fold into the cavity18starting from a specific air pressure (see dashed illustration of shutter24) and can therefore allow the oncoming fluid to flow into the cavity18. In one example, the elastic element27acan be a wound leaf spring which is attached at one end to the outer skin18of the aircraft100. For example, the shutter24can bear on the other end of the leaf spring. If, for example, a specific air pressure is present which corresponds to a pressure which is applied to the shutter in the case of a dive, the leaf spring yields and the shutter24folds into the cavity18of the sound-generating element12. The folded-in shutter24is shown by the dashed line. If the shutter24is folded in, the airflow can flow into the sound-generating element12, and a whistling sound is generated. In a further example, the elastic element can also be a conventional spring, in particular a compression spring,27a(see second schematic illustration on the right-hand side ofFIG. 3a) which is attached to the inner wall, and secures the shutter24from the inside. When the specific air pressure described above occurs, the spring yields, and an airflow can flow against the sound-generating element12.

In one example, as is illustrated schematically by way of example inFIG. 3b, the securing element26has a magnetic element27b, in order to secure the shutter24in a closed state. The magnetic element27bis dimensioned in such a way that in the event of a power loss the securing element no longer secures the shutter in a closed state, i.e. the magnetic element27bsecures the shutter24in the closed state as long as the magnetic element is supplied with power. In the event of a power loss or power failure, the magnetic element loses its effect and the shutter is no longer secured in the closed state and drops into an opened state. For example, the shutter24tilts away along the outer skin, i.e. the shutter24is mounted in such a way that the shutter24rotates for example into the plane of the drawing or out of the plane of the drawing along the outer skin14, with the result that the inlet16of the sound-generating element12is opened. In one example, a sliding layer29(e.g. a Teflon coating) could be arranged on the magnetic element27bor on the outer skin of the fuselage, with the result in the case of a power failure the shutter24can rotate away more easily. In another example, it is also possible to provide the shutter on one side with a weight or a tension spring or a compression spring, in order to permit or assist a rotational movement of the shutter into the plane of the drawing or out of the plane of the drawing, as soon as the magnetic effect of the magnetic element27bhas ceased.

In a further schematic illustration of the sound-generating element12inFIG. 3c, the blocking apparatus22is a film28. The film28is embodied in such a way that the film tears if there is a flow with a specific pressure against the film, wherein the specific air pressure occurs when there is an uncontrolled dive of the aircraft in the direction of the surface of the earth or if a specific speed value is exceeded. This specific speed value is dimensioned in this and in other exemplary embodiments in such a way that it preferably does not occur in the normal flying mode but only when there is an at least partially uncontrolled dive.

The film can preferably be arranged at the inlet16of the sound-generating element12. In one example, the film can be bonded onto the outer skin14. This has the advantage that the film is easily accessible and can easily be replaced when necessary, or its functional capability can be checked before each flight. For example, the film24can be checked for leakproofness or for correct seating at the inlet16and/or outlet20of the sound-generating element12. In the example shown here, the film28can also additionally be attached to the outlet20of the sound-generating element12. As a result, the sound-generating element12can be additionally protected against the penetration of moisture and dirt.

The embodiments inFIG. 3atoFIG. 3ccan be combined (not shown). The elastic element27a, the magnetic element27band the film28can, for example, be arranged together on the sound-generating element12. In this example, the film can ensure additional sealing of the elastic element27aand of the magnetic element27b. In one example, the attachment of the film28could be designed in such a way that an airflow tears the film off, and in a subsequent step the airflow flows against the elastic element and the magnetic element in such a way that the inlet is opened.

In addition, it is to be noted that “comprising” does not exclude any other elements or steps and “one” or “a” does not exclude a plurality. In addition, it is to be noted that features or steps which have been described with reference to one of the above exemplary embodiments can also be used in combination with other features or steps of other exemplary embodiments described above. Reference numbers in the claims are not to be considered restrictive.

LIST OF REFERENCE NUMBERS