CASING OF AN AIRCRAFT

The present invention relates to a casing intended to be externally applied, connected or fixed to the fuselage or to a wing of an aircraft or to a central or wing station/hardpoint of an aircraft, the casing entirely or partly delimiting a housing zone (HZ) of a super-orbital, orbital or sub-orbital launch vehicle.

TECHNICAL FIELD OF THE INVENTION

The present invention relates to a casing intended to be applied externally to an aircraft as well as an aircraft equipped with such a casing for containing a launch vehicle, in particular a super-orbital, orbital or sub-orbital launch vehicle.

STATE OF THE PRIOR ART

When a launch vehicle is air-transported, it can be inserted inside an aircraft or mounted externally to the latter.

In the first case, the launch vehicle is protected before launch by the surrounding environment defined by the aircraft's nacelle, but the release is complex, because it can interfere with the fuselage hatch, damaging the latter or being damaged if it is partially wedged out.

This would result in a displacement of the center of gravity of the aircraft outside the permissible limits and, in the case of launch vehicles based on liquid propellants, can cause contamination of the interior of the aircraft, with consequent risks of fire or explosion.

The external air-transported configuration, as reported for example in patents U.S. Pat. Nos. 4,901,949 or 7,458,544, is instead free from these problems, but it has the following problems.

First of all, the launch vehicle during all transport is exposed to the effect of the external environment, which mainly translates into the need for it to operate in an extremely wide range of temperatures, even down to −50° C., with consequent complexities depending upon the type of launch system.

Moreover, it is possible that an impact may occur with external objects, debris on the runway, birds, which could damage the launch vehicle.

It is then necessary to qualify or protect the launch vehicle from lightning.

It should also be taken into account that in the event of landing without a gear, the launch vehicle must first be detached from the aircraft with consequent loss of the launch vehicle itself in order not to interfere with the landing dynamics.

There is also a high sensitivity to weather conditions (hail) which could restrict the flight envelope.

Finally, in accordance with the external air-transported configuration, it is necessary to design the launch system to withstand the loads connected to the flight configuration and linked in particular to the presence of the fixing pylons and to the dynamics of the aerial platform which may involve a considerable increase in terms of inert mass of the air-transported system.

SUMMARY OF THE INVENTION

An object of the present invention is to provide a solution to the problem of transporting launch vehicles on aerial platforms, i.e. systems for accessing super-orbital, orbital and sub-orbital space.

Another object of the present invention is to provide a solution that allows super orbital, orbital and sub-orbital launch vehicles to be transported in a protected manner on an aircraft, substantially reducing the effect of external conditions such as for example the meteorological ones.

Another object of the present invention is to provide a solution as indicated above which ensures the transport of a launch vehicle on an aircraft under specific thermal conditions.

Another object of the present invention is to provide a solution as indicated above which allows a super-orbital, orbital or sub-orbital launch vehicle to be transported externally to an aircraft, substantially reducing the thermomechanical stresses to which the launch vehicle is subjected.

Another object of the present invention is to provide a solution that allows the transport on aerial platforms of super-orbital, orbital or sub-orbital launch apparatuses without the need to provide on the launch vehicles themselves interfaces (e.g. mechanical) depending upon the type of aerial platform.

In the accompanying drawings identical parts or components are indicated by the same reference numbers.

DETAILED DESCRIPTION OF THE INVENTION

With reference to the enclosed figures, a casing is shown intended to be externally applied, connected or fixed to the fuselage2aor to a wing2bof an aircraft2, such as airplane or glider entirely or partly delimiting a housing zone HZ of a launch vehicle3.

The casing is preferably constrained or anchored at the wing hardpoints or at a central hardpoint6of an aircraft.

In this text, “fuselage” means the main body part of an aircraft or airplane that contains passengers and/or cargo, depending on the type of aircraft. The fuselage can also house an engine or a tank inside, if required.

With “launch vehicle”, as it is known, it is to be intended a vehicle, such as a carrier rocket, propelled by a special type of engines, indicated as rockets or rocket engines, which vehicle is the means used to send for example in the space a given payload, which can include astronauts, satellites, interplanetary probes, refueling modules for orbiting space bases, etc.

A launch vehicle according to the present invention can of course be of the super orbital, orbital or sub orbital type, depending on whether it is designed to reach and then operate outside the Earth's orbit, on the Earth's orbit or within the zone defined by the Earth's orbit.

Preferably, the housing zone HZ is defined, in use, entirely between the casing1and a respective section of the outer wall of the fuselage2aof the aircraft2or of a wing2bor of a wing or central hardpoint6, whereby the casing1is in fact open at one of its ends or edges1a,for example annular and, in use, upper (seeFIGS.15,16and17) or lower (seeFIG.14), which end or edge is fixed, for example welded or glued or pivoted to the aircraft2or better to a wing or central hardpoint6of the same.

In this regard, preferably the casing1is connected by means of a coupling and release mechanism to a wing or central hardpoint6, which is fixed, if desired glued or mechanically connected, for example by means of fitting or forced insertion of parts, to an aircraft2or to a part of the fuselage2athereof.

The wing or central hardpoint6is in this case constrained, if desired also welded, glued or otherwise bound to the fuselage2aof the aircraft2or to a wing2bof the latter.

The wing or central hardpoint6is a rigid structural element, which, if desired, is faired.

An interface for the data and for the activation of opening and closing of the casing1or of a respective component1cis also preferably provided in the casing.

Alternatively, the casing1is substantially closed or closable and constrainable, externally to the housing area HZ, to the aircraft2, in which case the housing area HZ is defined entirely by the casing1.

Subject-matter of the present invention is also an aircraft2provided with a main frame or fuselage2a,with at least one wing2band at least one casing1according to the present invention as well as, if desired, with one or more launch vehicles3in each casing1

In such an aircraft2, the casing1is mounted externally to the main frame or fuselage2aor to a wing2band contains or is designed to contain a launch vehicle3outside the frame2aof the aircraft2, so as to protect the launch vehicle3during an entire flight phase of the aircraft itself.

Basically, the casing1is not a component of the fuselage or main frame2aof the aircraft2, but it constitutes an external element that is bound externally to the aircraft2or better to a wing or central hardpoint6of the same.

The casing1is designed to protect the launch vehicle3during an entire flight phase of a respective aircraft2.

The casing1can be made in any suitable way, for example with a curved wall or with a plurality of walls inclined to each other. It can be applied, connected or fixed to an aircraft2in any suitable way, for example pivoted or even partially welded or glued or even by inserting one or more of its parts in special guides defined by the aircraft2or by a respective wing or central hardpoint6or by fitting, forced insertion, snap engagement or bayonet engagement of respective portions of casing1and aircraft2or by any other suitable method.

Advantageously, the casing1includes heat-regulation means set to ensure a thermally stable and controlled environment in the housing zone HZ. Clearly, the heat-regulation means can be fixed to the aircraft2, but leading to or acting in the housing zone HZ.

The heat-regulation means can comprise a sensor designed to directly or indirectly detect the temperature in the housing area HZ and a heater and/or a cooler to adjust the temperature in the latter according to requirements or according to the data detected by the sensor.

Preferably, a first electronic connection data interface is provided between the launch vehicle3and the casing1. Even more preferably, a second electronic connection data interface is provided between the casing1and the aircraft2.

As indicated above, the casing1is preferably bound or connected to a wing or central hardpoint6through an anchoring mechanism, which is therefore a mechanical interface. In this interface, a special data interface can be provided or housed for the passage of data to activate any motor or monitor any sensors in the casing. The data interface may include, for example, a USB socket.

If desired, special means for the passage or transfer of electrical power to power one or more possible heaters, sensors, motors, actuators will also be provided in the anchoring mechanism. These means may include an electrical interface, such as a plug.

Preferably, the casing1is made of materials such as to deform externally and to resist internally so as to protect the launch vehicle3even in the event of landing without a landing gear allowing the aircraft2, such as an airplane, to land on its belly or on the respective lower part2cwithout the need to unload the launch vehicle in advance3.

The casing1can also be provided with control means, such as a pressure, temperature and/or environmental humidity sensor in the housing zone HZ. The casing1could then be equipped with sensors to connect it to the launch vehicle3to monitor the status of the latter. Clearly, the control means could also be fixed to the aircraft2, but leading or acting in the housing zone HZ.

If desired, the casing1or an aircraft is provided with a system for releasing a launch vehicle3located within the housing zone HZ.

Such release system includes means1b,1cfor closing-opening the housing zone HZ, a button or command means or electronic control unit for the opening-closing of the opening-closing means as well as one or more motors for actuating the closing-opening means1b,1c,so as to allow the opening or closing of the housing zone HZ according to the needs, for example an opening step during flight. The button or command means or electronic control unit is preferably on board the aircraft2or remotely operated, if desired from a control base.

According to a variant, the opening of the release system or of the respective opening-closing means could also take place or be controlled by gravity or by the action of springs or elastic elements and thus not necessarily through motors.

The closing-opening means1b,1ccan comprise doors of bomb-bay type, panels placed in the direction of the wind or counter-wind, single or multiple panels, detachable panels or panels which remain fixed to the aircraft and reclose the casing after the launch.

Basically, the casing1could have a part that can be fixed1b,by welding or other way to the aircraft2or better to the fuselage2aof the aircraft2and one or more doors or hatches1cmounted movable with respect to the fixable part1b.

The fixable part1bcould be for example annular and, if desired, with a curved extension defining a free section tapered away from the aircraft2or from a respective section of the fuselage of the latter. The fastening end or edge1aof the casing1to the aircraft2preferably constitutes an end or edge1aof the fixable part1b,this in particular when the casing1defines the housing zone together with a wall or section of wall of the fuselage2aor wings2bof an aircraft.

The hatch(s)1ccould be hinged to the fixable part1b,for example at a lower section or end1of the latter, so that by commanding the opening of the hatches1c,the launch vehicle is released downwards or falls. In this case, two movable doors1ccould be provided, hinged at their own distal end and with free end1eproximal and movable between a closed position, in which the free ends1eare adjacent to each other (seeFIGS.4and9) and an opening or release position of the launch vehicle3, in which the respective free ends1eare moved apart and are further lowered (seeFIGS.5and10) relative to the respective pivoting end1f.

The release means can alternatively be designed to release a launch vehicle3with a trim different than that of the aircraft2owing to a rotation in the release phase of the launch vehicle3with respect to the casing during the release phase.

Thus, for example, the casing1or a part thereof1ccan be pivoted in whole or in part to the aircraft2or to another component1bof the casing1. In this regard, a front or rear pivot axis could be provided.

According to the non-limiting embodiment shown inFIG.11, a hatch1cis provided hinged at one front end (i.e. closer, in use or after assembly, to the tip or front F of the aircraft2with respect to the other end) of the fixable part1b,whereby by activating the opening/closing means, by means of a respective motor, the inclination or angular displacement of the casing1or better of the respective hatch1cis caused, thereby making it possible the launch vehicle3to come out in the direction of the rear R of the aircraft2, more particularly owing to a sliding the launch vehicle3and releasing it in a direction from the front F to the rear R of the aircraft2.

As indicated above, hydraulic, spring actuators or even a cable damped release of the hatch1ccould be provided, and thus a system not necessarily driven by a motor.

Moreover, a cable or tie rod5could also be provided extending between a free end of the hatch1cand the fixable part1b,designed to ensure proper support and constraint of the hatch1cduring the opening phase of the same.

With regard toFIG.12, a solution similar to the one described above has been instead shown, but in such solution an anchoring point or pin4of the hatch1cis provided at one end, in use, front or rear of the casing1, so that by opening the latter, an initial constraint or pivot point of the launch vehicle3and thus a substantially vertical release or by falling of the launch vehicle3itself is determined. Clearly, the constraint point or pin4can be fixed or integral with the aircraft2, if desired with the fuselage2aor wing2bof the same, or with the casing1, if desired with a part1bof the same.

InFIGS.11and12, for illustrative purposes, the direction of advancement of the aircraft2and therefore of the respective casing1is indicated by A.

As it will be understood, also means for removable anchoring of the launch vehicle3to the casing or even to a section of the aircraft2could be provided, which removable anchoring means are designed to keep the launch vehicle3during flight and to release it, if desired after a hatch1cof the casing1has been opened or after opening or releasing the latter.

In this case, the removable anchoring means could be controlled by means of a pushbutton or command means or electronic control unit, for example on board the aircraft2or even remotely, if desired from a control base.

The casing1can also comprise support means7a,7bdesigned to minimize the loads induced by the flight or by the release of the launch vehicle3. The support means7a,7bcan include, for example, plate or tripod components mounted inside the casing1or on a surface, in use, internal1gthereof, defining the respective housing zone HZ and, if desired, defining resting seats7c,for example in recess for respective sections of the launch vehicle3.

Thus, for example, two or more (seeFIGS.1to3) plate components7a,which are suitably spaced, can be provided for supporting, in use, a front part and a rear part, respectively, of the launch vehicle3.

A single block component7bcan also be provided (seeFIGS.6to8) with a length corresponding to or slightly less than the launcher3.

The support means could be of a continuous cradle-like type or discontinuous with section capable of minimizing the mechanical stresses of a stationary or dynamic nature transferred to the launch vehicle3during the take-off, landing or cruise steps of an aircraft.

The support means could be made in several parts or in a single piece able to achieve the above indicated purpose.

The support means could be made of material compatible with the fluids present inside the launch vehicle3in order to prevent any thermal phenomena resulting from the tapping of the propellant.

Preferably, the support means7a,7bare integral and movable with one or more hatches1cof the casing, if this component is provided.

Moreover, support means of the launch vehicle3could also be provided following the opening of a hatch, for example a net or cables, which support means would be cut or broken in a step subsequent to the opening of the hatch.

If, for example, two hatches1care provided with a respective end1ethat can be removed for opening the housing zone HZ and releasing the launch vehicle, then the support means7a,7bwill preferably have several parts, each part being integral with a respective hatch1cand movable apart from each other so as to allow the launch vehicle3to be released or unfasten when the release system is operated.

Clearly, this expedient is not necessary, see for example the examples ofFIGS.11and12.

In this case, the launch vehicle3would be preferably only laying and not fixed to the support means7.

These support means7a,7bcan include supports made of plastic or rubber material or in any case material suitable for minimizing the loads transferred to the launch vehicle, if desired uniformly distributed along the lower surface of the housing zone HZ or distributed in sections along the housing zone HZ.

Clearly, the support means7a,7bdo not protrude outside the housing zone HZ and, if provided, beyond the end or edge1a.

The casing1could then be equipped with an appropriate fire-fighting system, and could be made of fireproof or self-extinguishing materials.

Advantageously, the casing1is made or internally covered with suitable chruncheable or compressible material8(seeFIG.13), e.g. multi-layer, in order to absorb energy in the case of landing of an aircraft without landing gear, protecting the launch vehicle therein in case of failure to release. The compressible material may include polymeric or metal structures, such as foamed metal or polymeric, which deform by absorbing energy in the event of an impact.

The casing1is made with thickness suitable to support the thermomechanical loads connected to the transport of the launch system. The casing can be the same for different aircrafts with different interfaces or can be made ad-hoc for a specific aircraft.

The casing can be made with a closed structure, pressurized as needed and equipped with any holes protected or not by valves for overpressure compensation, or for internal or external pressure balancing or for the release of any fluids deriving from accidental tapping.

Advantageously, the casing1is also equipped with appropriate diagnostics to monitor the internal state of the launch vehicle3and any tapping, such as for example optical diagnostics, level sensors and/or fluid sensors.

At least one sensor can also be present for monitoring the state of a launch vehicle3contained in the housing zone HZ. Such sensor can be fixed to the casing1or to the aircraft2.

Moreover, the casing could also have wings, as well as, if desired, a propulsion apparatus for autonomous flight once released from an aircraft2. To this regard, the casing could also have a parachute for the flight or controlled fall once released and optionally also or as an alternative motors for an autonomous flight or for a controlled glide.

Preferably, the casing1is made internally of materials compatible with the propellants used for the detonation of the launch vehicle and is thus also insensitive to any phenomena of tapping of the propellant, following the breakage of some fluidic component of the launching system or of a tank.

The casing1is also adapted to protect the launch vehicle3contained therein from any external phenomenon such as for example rain, hail, snow, impact with external bodies of any nature, lightning and any other type of phenomenon that could compromise the integrity of the launch vehicle3.

The launch vehicle3can possibly be released from the aircraft2in an emergency.

As far as the construction materials of the casing1are concerned, it can be made of any suitable material, for example metal, plastic, composite, ceramic or mixed material, if desired with fireproof protections.

Clearly, the casing1can be made with an aerodynamic shape designed to minimize the resistance to advancement and possibly intervene in a positive way on the lift of the aircraft2.

Of course, the casing can be used on any type of aircraft2, if desired with a single fuselage, double fuselage both below and above and in a configuration under the wing of an aircraft, as will be discussed later.

Moreover, the casing can also be equipped with an appropriate system for the release of the propellant on board the launch vehicle3in an emergency.

By aircraft according to the present invention it is meant, for example, aircrafts for transporting people, cargo, tankers or combat aircrafts.

A casing1according to the present invention can be constrained, in any suitable way, for example hinged or even partially welded or glued, or connected to a hardpoint through a suitable electromechanical interface, at any point outside the aircraft2, for example under the belly or portion of the lower wall2cof the fuselage2aof the aircraft2(seeFIGS.15,16and17), under a wing2bof the aircraft2or above a portion of the upper wall2dof the fuselage2a(seeFIG.14).

As it will be possible to ascertain, a casing1according to the present invention guarantees a protected transport (from external objects, lightning, etc.) of launch vehicles on an aircraft.

Moreover, owing to the present invention it is possible to obtain a transport of a launch vehicle on an aircraft under specific thermal conditions as well as subjecting it to various controls during the flight impossible to carry out with the solutions according to the prior art.

A casing according to the present invention can also allow landing without gear of a respective aircraft without the need to detach the launch vehicle in advance.

Changes and variants of the invention are possible within the scope defined by the claims.