ITPI20090126A1 - AIRCRAFT WITH QUICK RELEASE DEVICE FOR THE FUSER AND CONTROL IN THE LAND OF THE SAME. - Google Patents

Description

TITLE

Description accompanying the patent application for industrial invention entitled:

AIRCRAFT WITH A QUICK RELEASE DEVICE OF THE

FUSELAGE AND LANDING CONTROL OF THE SAME

Scope of the invention

The present invention relates to the aeronautical technical sector.

In particular, the invention refers to an innovative and revolutionary structural concept of aircraft capable of coping with crisis and emergency situations through a construction with one or more detachable modules.

Brief notes on the known art

The history and evolution of aeronautics quickly led us from the first and rudimentary experimental aircraft to modern transport aircraft, both civil and military, with ever greater safety margins. By now the use of airplanes for civil transport has become an absolute necessity and an ordinary and daily fact to the point that it is no longer reserved for a narrow â € œelità ̈â € of people.

For this reason, the need for safety in flight is increasingly felt and aeronautical engineering strives towards this direction. The use of new design concepts therefore makes it possible to predict and minimize damage due, for example, to the well-known phenomena of structural fatigue, all together with support instruments and increasingly sophisticated investigation techniques.

However, despite the continuous efforts to do so, the catastrophic event is always lurking. Sometimes the inauspicious event can be caused by an engineering fault or human negligence, for example when a certain "scheduled check" of inspection is not carried out with due expertise. In other cases, the unfortunate event may not be foreseeable, such as an impact with a foreign body in flight, such as a bird or even an incorrect maneuver. The accident cases, whether due to human error or not, are unfortunately consistent.

When this happens, the recovery of the aircraft and the rescue of the people on board is very difficult and unlikely. Once the pilot loses all control and the aircraft falls inexorably, the only possible maneuver is to attempt a glide. However, the strong impact with the ground, even if it is not always a direct cause of passenger death, becomes so due to subsequent explosions and fires due to fuel and engines.

Parachute systems for small aircraft are currently being tested. However, this solution is not only not yet under study and is limited, for obvious weight reasons, only to small aircraft, such as touring ones.

Summary of the invention

It is therefore an object of the present invention to provide a new concept of aircraft in general which overcomes the safety drawbacks mentioned above.

In particular, it is an object of the present invention to provide an aircraft built according to a concept with one or more detachable modules, to allow the rescue of people even in critical conditions.

It is therefore an object of the present invention to provide an aircraft whose module detachment control may also take place remotely, for example from a control tower or from another authorized aircraft, in such a way as to intervene in the event of the pilot's inability to operate. .

It is also an object of the present invention to provide an aircraft which can be controlled remotely in order to further inhibit any attempts of a terrorist nature.

These and other objects are therefore achieved with the present aircraft, as per claim 1.

In particular, in accordance with the present invention, an aircraft is provided configured in such a way as to provide at least one module (3) used for the transport of persons and / or goods which can be selectively detachable from the remaining part (2) of the aircraft (1) and in which the module (3) comprises means (11, 12) for allowing to control the descent after detachment.

In this way, in any irreversible risk condition, it is possible to operate the detachment of the aforementioned module that transports people from the rest of the aircraft. It is therefore possible to avoid the risk of explosions and fires due to the fuel contained in the wings or engines at the moment of impact, as well as the possibility of a safe landing or ditching by maneuvering the vehicles (11, 12).

Advantageously, the means (11, 12) comprise bearing surfaces (11) of the extractable and / or parachute type (12) and in which the bearing surfaces (11) are configured in such a way as to allow a control of the module at least in the first subsequent phase to posting.

In this way it is possible to exploit the surfaces carried in a first phase of control of the detachment and subsequently complete the descent following the extraction of the parachutes.

Advantageously, the parachutes (12) can be arranged inside the module and can be selectively activated after detachment in such a way as to slow down the descent speed.

In addition, despite the presence of the parachutes and the bearing surfaces 11, it is also possible to provide at the base of the module, or where necessary, a plurality of air-bags to ensure a more cushioned impact.

Advantageously, in order to connect the module 3 to the rest of the aircraft, hooking / unhooking means are provided. The vehicles are therefore selectively operable from a gripping condition, in which the module (3) is bound to the rest of the aircraft (2), to a release condition in which the module is released from the rest of the aircraft (2).

Among the various possible constructive solutions, the coupling / release means can comprise at least one of the following solutions chosen:

- Explosive head bolts;

- Coupling systems that can be operated between a gripping position and a release position.

Advantageously, the module (3) is configured in such a way that the disconnection takes place in at least one of the following ways:

- By receiving a remote remote control;

- Through the direct command of the pilot.

The remote control solution is particularly advantageous as it is effective in inhibiting any attempt at terrorist piracy.

The module solution therefore preferably provides a second support module (2) for at least the propulsion means and the bearing surfaces (8, 9), said second module being configured in such a way as to be coupled to the first module (3).

In this case, preferably, the second module (2) can comprise a central body (2) in the form of a cap (2), preferably but not necessarily of the cylindrical type, in such a way as to overlap the first module (3), said superposition making a first (4) and a second shell (2, 5) superimposed.

In particular, an additional pressurization cushion can be provided between the inner shell (4) and the outer shell (2, 5).

Advantageously, the remaining part of the aircraft can also comprise a plurality of parachutes (12â € ™) arranged inside and selectively operable after detachment from the module (3).

Brief description of the drawings

Further characteristics and advantages of the present aircraft, according to the invention, will become clearer with the following description of an embodiment thereof, given by way of non-limiting example, with reference to the attached drawings, in which: - Figure 1 shows in section the aircraft made through the combination of two detachable modules (3) and (2);

- Figure 2 shows an axonometric view of the two detached modules.

- Figure 3 shows a section of the two coupled modules.

- Figure 4 shows an axonometric view of the two coupled modules;

- Figure 5 shows an example of detachment of the module (3) from the module (2) with the simultaneous release of control surfaces 11;

- Figure 6 shows a subsequent phase of releasing safety parachutes 12 and 12â € ™.

Description of a preferred embodiment With reference to figure 1 and figure 2, a section and an axonometric view of an aircraft are highlighted respectively 1. According to the invention, the aircraft comprises a module 3 used for the transport of persons and / or cargo and configured in such a way as to be selectively detachable from the remaining part 2 of the aircraft 1.

In particular, the module 3 is in the form of a shell and replaces the classic conventional fuselage. The module 3 (see section of figure 1) can therefore foresee, in accordance with the classical construction technologies, common ordered spaced apart and covered with riveted panels in order to realize the internal shell 4. The classic beam of keel which is actually used for the construction of the walkable floor 6.

The inner shell, as will be better detailed in the following of the present description, can comprise a second outer covering 5 which partially surrounds the shell 4 (see also section of figure 2). Also module 3 therefore provides for the cockpit 7, that is the cockpit, equipped with the common instrumentation necessary for the flight in addition to the windows and internal seats for passengers (therefore completely similar to the common fuselage).

The view of figure 2 shows module 3 detached from the rest of the aircraft.

In particular, a second module 2 is therefore configured in such a way as to aerodynamically perform the main flight functions. In this sense it includes the wings 8, the tail planes 9, any rudders and the propulsion means or the engines. It is however evident how the geometries, the positioning and the number of components included in this second module can be practically infinite, and without thereby departing from the present inventive concept. For example, the wings can easily be placed in a more or less forward or backward position and equipped with all the necessary control surfaces. The same goes for propulsion and rudders. Furthermore, the tail planes, as well as the engines or the wings themselves, can be provided in several independent modules.

Returning to the section of Figure 1, the second module therefore comprises a central body 2 in the form of a cap 2, for example cylindrical, to which the wings, engines and tail planes are connected. In this sense, the second module externally reproduces the normal profile of each aircraft. The internal radius R of the cap 2 is such that it overlaps the module 3 along the contact line created by the thickness 5.

Other forms of cap of a different nature to the cylindrical one can be produced without thereby departing from the present inventive concept.

The section of figure 3 therefore shows the structural result of this coupling between module 2 and module 3. In particular, the constructive solution described above shows how, following the coupling, a double shell is created (4, 2-5 ) consisting of the inner shell 4 and the outer shell obtained by combining the second coating 5 with the cap 2.

The space gap interposed between the two internal 4 and external shells (2, 5) can then be further pressurized at will by means of common pressurization means similar to those of cabin pressurization.

This solution, if adopted, is extremely advantageous as it allows to reduce the pressure difference value to which the shell is subjected 4. The interposed pressurization creates a reduction in the pressure jump between the outside of the aircraft and the inside the shell 4. On the one hand, this allows to reduce the thickness of the shell (and therefore to minimize the weights) and at the same time to increase the fatigue life of the shell itself. Furthermore, the presence of a double shell guarantees redundant safety thicknesses.

As also shown in figure 5, module 2 naturally provides a suitable window 10 which overlaps the â € œcockpitâ € 7 (together identifying the cockpit 7) of module 3 and a plurality of portholes. In this way, after coupling, the pilot can easily see outwards as well as the passengers.

The constructive solutions that can be implemented in order to obtain coupling / release means which connect the two parts in a selectively detachable manner can be of various kinds.

For this purpose, suitable explosive bolts can be designed, for example, so that the pilot or a user external to the vehicle (for example the remote control tower), has the ability to explode them in order to allow detachment. Other equivalent solutions can provide coupling systems which can be operated between a gripping position and a release position.

As described in the following figure 5, the module 3 provides means (for example simple pneumatic or hydraulic actuators commonly used in the aeronautical field) which command the release of suitable control surfaces 11. The surfaces 11 are in fact stabilizing wings which allow the pilot to check at least the first phase of detachment of module 3 from module 2. A suitable wing surface could possibly guarantee an entire gliding phase.

In this sense, the surfaces 11 can therefore have any surface value deemed suitable for the purpose as well as provided with further moving parts in order to make the module more manageable.

As then described in Figure 6, the module 3, and possibly also the module 2, can then be further provided with suitable parachutes 12 and 12â € ™ arranged within the structure of the modules themselves and can be activated after the release.

In this way, after the first release phase, the activation of the parachutes guarantees a completely safe landing for the occupants of the vehicle.

The parachutes can then be operated in multiple equivalent ways. For example, the parachutes 12â € ™, relative to the second module 2, can be opened by arranging a piston opening system for their housings, following a release signal. In the same way, once module 3 has been settled, the opening of the lodgings relating to the parachutes 12 can be commanded.

Appropriate air bags outside the module 3 and inside the passenger and crew seats can be further provided to ensure a safer landing.

The detachment command of module 3, ie the activation of the coupling / uncoupling means, can take place remotely or, naturally, through a command from the pilot. The remote solution (for example from a control tower or another aircraft) is very efficient in avoiding terrorist attacks. Any attempt at sabotage is blocked by the activation of the detachment of module 3 which can be activated by any control tower or by any authorized aircraft (for example a fighter).

The present description naturally refers, without any limitation, to an aircraft in the most generic sense of the term including civil and military aircraft of any shape, nature and size.

Claims (10)

CLAIMS 1. An aircraft characterized by the fact that it is configured in such a way as to include at least one module (3) used for the transport of persons and / or goods, which can be selectively detachable from the remaining part (2) of the aircraft (1) and in which the module (3) also comprises means (11, 12) to allow its descent to be controlled after detachment. 2. An aircraft, according to claim 1, in which said means (11, 12) comprise bearing surfaces (11) of the extractable and / or parachute type (12) and in which the bearing surfaces (11) are configured in such a way as to allow a control of the module at least in the first phase following the detachment. 3. An aircraft, according to claim 2, in which said parachutes (12) are arranged inside the module and can be selectively operated after the detachment to brake the descent speed of the module. 4. An aircraft, according to one or more preceding claims, in which coupling / release means are provided for connecting said module (3) to the remaining part of the aircraft (2) and in which said means are selectively operable from a condition of socket, in which the module (3) is linked to the rest of the aircraft (2), in a release condition in which the module is released from the rest of the aircraft (2). 5. An aircraft, according to claim 4, in which said coupling / uncoupling means comprise at least one of the following solutions at your choice: - Explosive head bolts; - coupling systems that can be operated between a gripping position and a release position. 6. An aircraft, according to claim 1, in which the module (3) is configured in such a way that said detachment takes place in at least one of the following ways: - By receiving a remote remote control; - Through pilot command. 7. An aircraft, according to claim 1, in which a second support module (2) is provided for at least the propulsion means and the bearing surfaces (8, 9), said second module being configured in such a way as to be coupled to the module (3). 8. An aircraft, according to claim 7, wherein said second module (2) comprises a central body (2) in the form of a cap (2) in such a way as to overlap the first module (3), said overlapping forming a first (4 ) and a second shell (2, 5) superimposed. 9. An aircraft, according to claim 8, in which a pressurization cushion is provided between said inner shell (4) and said outer shell (2, 5). 10. An aircraft, according to one or more preceding claims, in which the remaining part (2) of the aircraft (1) comprises a plurality of parachutes (12â € ™) arranged inside and selectively operable after detachment from the module ( 3).