Patent Description:
In the field of aerial photography or reconnaissance by sensors, sensing means and/or cameras mounted on board an aircraft are used and directed so that, during flight, they point towards the ground in order to carry out the required surveys and reconnaissance. In particular, in airplanes equipped with a pressurized cabin which may be reconfigured for multi-mission purposes (e.g., maritime surveillance, transportation of cargo or products, transportation of personnel or passengers, search and rescue missions), the installation of sensing means or cameras is provided for remote sensing at altitude on an external surface of a fuselage facing the ground, or on an opening hatch, or on an opening window, so that the sensors or cameras may be exposed directly to the outside without the detection passing through glass, degrading the quality of the sensing signal which is for example optical or radio.

Indeed, the sensing means and cameras, due to their inherent characteristics of operation, need to be pointed directly at the ground, without any interference in the visible and non-visible range, such as refraction and/or reflection phenomena through the transparent parts of the aircraft (such as windows, etc.).

Airplanes, especially those for cargo, or which are at least partly assigned to transport cargo, often have cramped spaces and require distinctive, specific, and complex installations to be applied on the platforms that support the sensing means, or cameras. Indeed, in order to allow the sensor to exit the aircraft through a port during the unpressurized flight, a mechanical arm is used in many applications, which results in the use of space on the aircraft and has repercussions on the vibrational performance that need to be properly compensated for.

All this has major consequences on the reconfigurability and stowage of the equipment on which the sensing means are mounted after use.

Examples of further known aircrafts with means to deploy sensing means are shown in the patent applications <CIT> and <CIT>, and in the US patent <CIT>.

The arrangements of sensors generally used in aircraft according to the prior art, such as the one just described, have several drawbacks.

First, the known arrangements require a large volume to move the sensors and therefore create a large footprint inside the aircraft. In particular, in the arrangements according to the prior art, when the use of the sensing means is no longer necessary, the area or bay in which the sensing means are arranged during use may still not be reused.

In addition, if the sensing signal from the sensing means is not able to reach the ground directly except by passing through a transparent part (such as a window or windowed hatch), the quality of the signal and consequently the sensing will be compromised, due to the aforementioned refraction and/or reflection problems.

The object of the present invention is to provide an aircraft with a moving system for moving sensing means that does not have the drawbacks of the prior art.

This and other objects are fully achieved according to this invention by an aircraft as defined in the appended claim <NUM>.

Advantageous embodiments of the invention are specified in the dependent claims, the content of which is to be understood as an integral part of the description that follows.

In short, the invention is based on the idea of providing an aircraft comprising:.

Advantageously, the moving system may further comprise drive means adapted to actuate the sliding movement of said slide along the direction of movement. Preferably, said drive means may comprise a handle which is arranged integrally with the slide and adapted to allow the manual movement of the slide and/or at least one actuator, preferably an electric actuator or a hydraulic actuator.

Preferably, moreover, the moving system may comprise an abutment element arranged so as to limit the sliding movement along the direction of movement of the slide, or so that the slide abuts the abutment element when the sensing means are in said work position.

Advantageously, the moving system may further comprise a ramp arranged integrally with the abutment element and facing towards said slide, and a caster mounted rotatably on a pin arranged on the slide, wherein the caster is adapted to come into contact with said ramp to facilitate or direct the sliding movement of the slide along the direction of movement.

Advantageously, moreover, the abutment element may have a tilted part which is adapted to cooperate with a draw part of a guide of the pair of guides, or with an edge of the slide, to guide the sliding movement of the slide along the direction of movement.

Preferably, the moving system may further comprise a plurality of dampers which are arranged on said slide, or arranged on said slide and interposed between said slide and the sensing means, and are adapted to dampen or limit the transmission of vibrations to the sensing means.

Preferably, the moving system may further comprise a blocking element which is arranged integrally with the abutment element and adapted to be arranged in a blocking configuration wherein it blocks the movement of the slide along the direction of movement.

Preferably, in the aircraft according to an embodiment of the invention the sensing means are arranged on the slide of the moving system and integral thereto in the sliding movement along the direction of movement.

Preferably, the sensing means may comprise one or more among: optical sensors, a radar sensor, lidar sensors, remote sensing sensors, temperature sensors, Doppler-effect sensors, spectral sensors or hyperspectral sensors.

Finally, preferably, the aircraft or fixed-wing aircraft according to an embodiment of the invention further comprises a structure, such as a fuselage, having an opening which preferably faces the ground when the aircraft is in flight and is capable of connecting the interior and exterior of the aircraft, the opening being openable and closable by means of a hold door;
wherein in the work position the sensing means face directly towards the outside of the aircraft through said opening and the opening is open.

The features and advantages of the present invention will be clarified by the detailed description that follows, given purely by way of non-limiting example and with reference to the attached drawings, in which:.

With reference to the figures, in general, the aircraft according to the invention is generally indicated with <NUM>. The aircraft (known per se, not fully shown in the figure but only the part relevant to the invention) comprises a sensing system <NUM>, which in turn comprises a moving system <NUM> and sensing means <NUM>. The moving system <NUM> is adapted for use when the aircraft <NUM> is in flight to move sensing means <NUM> of the aircraft between the two positions as defined above, or a rest position, in which the sensing means <NUM> are arranged or stowed inside the aircraft <NUM> or a structure <NUM> of the aircraft, such as, for example, a fuselage, and a work position, in which the sensing means <NUM> face directly, along a sensing direction y (described in more detail below), towards the outside of the aircraft <NUM> and towards the ground when the aircraft <NUM> is in flight.

The moving system <NUM> essentially comprises a frame <NUM>, a slide <NUM> and a pair of guides <NUM>.

The frame <NUM> is made in a manner known to the person skilled in the art, preferably of metal or composite material. The frame <NUM> is arranged internally to the aircraft <NUM>, or it is arranged fixed with respect to the inner structure of the aircraft <NUM>, e.g., it is attached thereto by conventional mechanical connection means, such as threaded mechanical connection means. As clearly visible in <FIG>, and in <FIG>, the frame <NUM> may be made in the shape of a squared C and may have a pair of parallel parts 12a and 12b joined by a transverse part 12c. The component parts of the frame <NUM> may, for example, be made as lattice trusses.

Preferably, the frame <NUM> is made and appropriately sized so that it may be arranged in place of guides or sliding seat supports of the aircraft <NUM>, for example, it is sized to occupy the same footprint in width as a seat or pair of adjacent seats. In this way, it is possible to easily and quickly reconvert, even temporarily, the interior space of the aircraft <NUM>.

The guides <NUM> of the pair of guides <NUM> are preferably arranged parallel to each other and spaced apart. Preferably, each guide <NUM> is mounted on one of the parallel parts 12a and 12b of the frame <NUM>. There is nothing to prevent the number of guides <NUM> from being different, as is evident to the person skilled in the art; for example, a pejorative but still feasible solution of the invention involves the use of only one guide <NUM>. Alternatively, it is also possible to strengthen the moving system <NUM> according to the invention by using two pairs of guides <NUM> arranged two on one side and two on an opposite side of the frame <NUM>. In the embodiment shown in the figures, the guides <NUM> are arranged below the slide <NUM> and support it from below, but it is also possible to arrange the guides <NUM> above the slide <NUM> and mount the slide <NUM> hanging or hooked onto the guides <NUM>, without thereby departing from the scope of the invention.

In particular, as is clearly visible in <FIG>, each of the guides <NUM> is made as a telescoping guide, or it has a fixed part and one or more draw parts, or arranged slidable one on top of the other, and the first of said draw parts is mounted slidable on the fixed part. According to the invention, each guide <NUM> comprises a rail part 16a and a draw part 16b, and the draw part 16b of each guide <NUM> is arranged slidable relative to the relevant rail part 16a along a direction of movement x, which is essentially perpendicular to said sensing direction y. It is clear to the person skilled in the art that the rail part 16a may be configured as a track guide or as a monorail guide. It is also clear to the person skilled in the art that a guide <NUM> used in the invention may also have a different number of additional draw parts 16b arranged slidable on a preceding draw part 16b. In the embodiment shown in <FIG>, each guide <NUM> has a rail part 16a arranged on one of the parallel parts 12a or 12b of the frame <NUM>, a first draw part 16b mounted slidable on, and relative to, the rail part 16a, and a second draw part 16b' mounted slidable on, and relative to, the first draw part 16b.

Preferably, the relative sliding of the draw part(s) 16b and 16b' is facilitated by the provision of suitable anti-friction means, such as ball bearings interposed between the draw part(s) 16b and 16b' and the relevant guide part <NUM> on which they slide, or an additional draw part 16b or the rail part 16a.

The slide <NUM> is adapted to support the sensing means <NUM>. In the example embodiment shown in <FIG>, the slide <NUM> is made as a drawer, or as a supporting surface in the form of a slidably mounted plate. The slide <NUM> is mounted so that it may slide relative to the frame <NUM> along said direction of movement x inside the aircraft <NUM> to move the sensing means <NUM> which it carries between the rest position and the work position. Specifically, for this purpose, the slide <NUM> is mounted integral to the draw parts 16b of the guides <NUM>, or it is mounted integral on the last of the draw parts 16b of each guide <NUM>, so that when each telescopic guide <NUM> is fully pulled out, the slide <NUM> is brought to a position of maximum distance from the frame <NUM>.

To enable the translation movement of the slide <NUM> adapted to bring the sensing means <NUM> between the rest position and the work position, the moving system <NUM> preferably further comprises drive means <NUM> adapted to actuate said movement along the direction of movement x. Specifically, the drive means <NUM> may comprise a handle <NUM>, or a hollowed-out or lowered part, arranged integral to the slide <NUM>, to allow an operator to pull or push the slide <NUM> manually along the direction of movement x. The drive means <NUM> may also comprise at least one actuator (not shown, known per se), for example a hydraulic actuator, an electric actuator, or a pneumatic actuator, to enable the movement of the slide <NUM> along the direction of movement x to be controlled in a motorized and/or automated manner. In a preferred embodiment, the drive means <NUM> may comprise both a handle <NUM> and at least one actuator, so as to achieve functional redundancy. Preferably, when present, the at least one actuator is remotely controllable through control means, such as through a button arranged in a cockpit of the aircraft.

As is particularly visible in <FIG>, the moving system <NUM> according to a preferred embodiment of the invention further comprises an abutment element <NUM>. The abutment element <NUM> is arranged in such a way as to limit the sliding motion of the slide <NUM> along the direction of movement x, for example by providing a stop or striker surface against which the slide <NUM> abuts when the sensing means <NUM> have been brought into the work position. Alternatively, the abutment element <NUM> may consist of a plurality of striking surfaces, for example a plurality of small cylinders or walls arranged aligned with each other.

As may be seen in <FIG>, and in <FIG> in detail, the abutment element <NUM> may, for example, be made by means of two small walls which are arranged on two opposite sides in such a way as to define two abutment surfaces against which one edge of the slide <NUM> abuts, and which are fixed in place by conventional mechanical means of connection known to the person skilled in the art.

Advantageously, the moving system <NUM> further comprises a ramp <NUM> and a caster <NUM>, which are adapted to cooperate with each other to facilitate the sliding movement of the slide <NUM> along the direction of movement x.

For this purpose, the ramp <NUM> is arranged integral with the abutment element <NUM> or otherwise integral with the internal structure of the aircraft, and is mounted facing the slide <NUM>. The caster <NUM>, on the other hand, is rotatably mounted on a pin <NUM>, which is arranged on the slide <NUM>.

In fact, as the slide <NUM> carries the sensing means <NUM> in its movement as the slide <NUM> is moved along the direction of movement x, and the sensing means <NUM> move away from the frame <NUM>, or the rest position, and closer to the work position, the weight of the sensing means <NUM> may cause it to bend (directed downward, in <FIG> and <FIG> - and stylized with the arrow F in <FIG> and the bottom part of <FIG>), which risks preventing the slide <NUM> from completing its movement along the direction of movement x.

Thus, as shown in the bottom part of <FIG>, when the slide <NUM>, moving away from the frame <NUM>, is approaching the abutment element <NUM>, the caster <NUM> makes contact with the tilted surface of the ramp <NUM> and allows the routing of the slide <NUM> and thus facilitates the remaining part moving along the direction of movement x, shown in the top part of <FIG>.

Clearly, the relative arrangements of the caster <NUM> and ramp <NUM> may also be reversed without departing from the scope of the invention.

The ramp <NUM> is preferably made of, or its surface is covered with, a material with a low or very low friction coefficient, such as polytetrafluoroethylene.

Clearly, the ramp <NUM> may also be equivalently replaced by a curved structure, or which has a curved surface, for example in the shape of a duckbill, and is in any case made in such a way as to facilitate the ascent of the caster <NUM> on its surface.

In the preferred embodiment shown in the figures, the moving system <NUM> comprises a pair of casters <NUM> and a pair of ramps <NUM> as described above, arranged at opposite sides with respect to a centerline of the sensing means parallel to the direction of movement x, each of the casters <NUM> being adapted to cooperate with a relevant ramp <NUM> of the pair of ramps.

Finally, as is clear to the person skilled in the art, moreover, further mechanisms not explicitly described here but known to the person skilled in the art may also be implemented for the purpose of facilitating, or directing, the movement of the slide <NUM> along the direction of movement x.

Preferably, moreover, the abutment element <NUM> may have a tilted part <NUM> to further facilitate the routing of the movement of the slide <NUM> along the direction of movement x. In particular, the tilted part <NUM> may be configured to cooperate with a draw part 16b of one of the guides <NUM>, or with an edge of the slide <NUM> so as to guide the sliding movement of the slide <NUM> along the direction of movement x.

Preferably, moreover, the moving system <NUM> comprises at least one blocking element <NUM> which is arranged integral with the abutment element <NUM> and adapted to be arranged in a blocking configuration where it blocks the movement of the slide <NUM> along the direction of movement x. As shown in <FIG>, in a purely illustrative and non-limiting embodiment, the blocking element <NUM> may comprise a pin <NUM> that may be placed within a corresponding hole <NUM> made in a side edge of the slide <NUM> and/or on the draw part 16b of one of the guides <NUM>. Alternatively, the blocking element <NUM> may be made as a hook or other conventional configuration.

As shown in <FIG>, the moving system <NUM> may also comprise a directional pin <NUM>, which is adapted to cooperate with a corresponding hole <NUM> made in an edge of the slide <NUM> and/or on the draw part 16b of one of the guides <NUM>.

As mentioned above, the moving system <NUM> may be used in a sensing system <NUM>. The sensing system <NUM> comprises, in addition to the moving system <NUM> according to any of the above-described embodiments, sensing means <NUM> arranged on the slide <NUM> so as to be integral therewith in the sliding movement along the direction of movement x. Preferably, a plurality of dampers <NUM> is arranged on the slide <NUM>, and interposed between the slide <NUM> and the sensing means <NUM>. Said dampers <NUM> are adapted to dampen the vibrations transmitted to the sensing means <NUM> so as to improve the stability of the positioning of the sensing means <NUM> and consequently the quality of sensing of the sensing means <NUM>. The person skilled in the art will be able to select appropriate dampers <NUM> depending on the load, or the vibrations transmitted to the slide <NUM> and, therefore, to the sensing means <NUM>, as well as the type of aircraft and the type of mission.

The sensing means <NUM> are generally facing downward in <FIG>, <FIG> and <FIG>, or towards the ground when the aircraft is in flight, thus defining the sensing direction y mentioned above.

The sensing means <NUM> may comprise at least one of: video cameras, cameras, optical sensors, a radar sensor, lidar sensors, remote sensing sensors, temperature sensors, Doppler-effect sensors, spectral sensors or hyperspectral sensors. Essentially, therefore, the sensing direction y of the sensing means <NUM> is the direction towards which the emission of the sensing means <NUM> is oriented, for example the direction towards which the laser is oriented, if the sensing means <NUM> are comprised of laser sensors, or the direction towards which the lens is oriented, if the sensing means <NUM> are comprised of a camera, and so on. In any case, the sensing means <NUM> may comprise any type of sensor that is useful for conducting remote sensing at altitude from aircraft and adapted to withstand the displacements resulting from moving the slide <NUM> along the direction of movement x.

As mentioned above, the sensing system <NUM> may be mounted on the aircraft <NUM> according to the invention, or a fixed-wing aircraft, preferably an airplane. As mentioned above, the aircraft has a structure <NUM>, such as a fuselage, which is preferably pressurizable, and in which an opening <NUM> is defined. The opening <NUM> is intended to connect the interior and exterior of the aircraft or structure <NUM> of the aircraft. The opening <NUM> may be closed and opened by a hold door <NUM>, for example a hold door <NUM> mounted so as to be hinged and pivotable along one of its side edges. By virtue of the moving system <NUM>, the sensing means <NUM> of the sensing system <NUM> may then be moved between the rest position and the work position, in which they face directly towards the outside of the aircraft. In a mode of use, or in a flight phase, preferably at low altitude, in which the aircraft's mission involves a remote sensing operation by the sensing means <NUM>, the hold door <NUM> is brought into an open configuration and the opening <NUM> is therefore open. At this point, an operator may use the drive means <NUM>, such as the handle <NUM>, to move the slide <NUM>, and consequently the sensing means <NUM> attached thereto, to the work position, or to bring the slide <NUM> to the open opening <NUM> and thus position the sensing means <NUM> to face directly towards the outside of the aircraft. The sensing signal, which, as mentioned above, defines the sensing direction y, of the sensing means <NUM> may then pass freely through the open opening <NUM> without having to penetrate any means, not even a transparent means such as a glass or window, and define a detection cone C (shown with dashed lines in <FIG>).

As may be seen from the preceding description, by virtue of the moving system of the aircraft according to the invention, the objects of the above-described invention may be fully achieved, resulting in several advantages.

First of all, with said moving system, sensing means may be easily moved on an aircraft, while still ensuring that the moving system has the smallest possible footprint inside the aircraft and is easy to implement.

Furthermore, by virtue of the possibility of sizing the moving system and the sensing system all according to the lateral footprint of one or more seats, it is possible to use the same space occupied by one or more seats, easily reconfiguring it by mounting said sensing system in place of the one or more seats.

Finally, by virtue of the configuration of the aircraft, it is possible to place the sensing means in such a way that a sensing signal therefrom may be disseminated to the ground and to the aircraft's external environment without having to pass through means, even transparent means, such as windows or glass, and therefore without having to tolerate degradation or reduction in signal quality.

Claim 1:
Aircraft (<NUM>) comprising:
- sensing means (<NUM>);
- a moving system (<NUM>) adapted for use when the aircraft (<NUM>) is in flight to move the sensing means (<NUM>) of the aircraft (<NUM>) between a rest position, wherein the sensing means (<NUM>) are arranged inside the aircraft (<NUM>), and a work position, wherein the sensing means (<NUM>) face directly, along a sensing direction (y), toward the outside of the aircraft (<NUM>) and toward the ground when the aircraft (<NUM>) is in flight, the moving system (<NUM>) comprising:
- a frame (<NUM>) arranged inside the aircraft (<NUM>);
- a slide (<NUM>), adapted to support said sensing means (<NUM>); and
- a pair of guides (<NUM>), each comprising a rail part (16a), supported on said frame (<NUM>), and at least one draw part (16b; 16b'), the draw part (16b; 16b') of each guide (<NUM>) being arranged telescopically slidable relative to the respective rail part (16a) along a direction of movement (x) which is essentially perpendicular to said sensing direction (y);
the slide (<NUM>) being mounted integrally with the draw parts (16b; 16b') of the pair of guides (<NUM>) in such a way to slide along the direction of movement (x) inside the aircraft (<NUM>) to move said sensing means (<NUM>) between said rest position and said work position.