AIRCRAFT SAFETY DEVICE

Abstract

- AIRCRAFT SAFETY DEVICE - This aircraft safety device transforms the fuselage into an emergency module in the event of damage [Fig.42]. There are three parts, the fuselage, the wings, and the elevator, [Fig.26]. They can be separated from each other, each of its parts grouping sub-devices which ensure this transition. The first part of this assembly, (the fuselage) represents the emergency module. This one has a Sigma device [Fig.30] which is composed of two ailerons. They have the particularity of blending into the mass of the wings of the aircraft of part 2 [Fig.28][Fig.29]. This emergency module integrates an Alpha device, [Fig.7] of two stabilizers which have the role of relay elevator. In the fuselage, there is a Theta device [Fig.30] composed of four fans distributed judiciously on each side of it hidden inside a dedicated compartment; and whose main function is to slow the fall of this rescue module, if necessary, but we can attribute other possibilities to it. This rescue module includes an Iota device [Fig.38][Fig.40], hatches which serve as landing gear, to cushion the impact on the ground and guarantee a horizontal plane whatever the type of terrain encountered. The second part of this assembly serves as a reception base for the rescue module. As for the third part of this assembly (the elevator) [Fig.41] [Fig.53] it is a drone whose mission is to tow this rescue module or to participate in rescue searches. FIGURE FOR ABBREVIATION: [Fig.3].

Description

Title of the invention: AIRCRAFT SAFETY DEVICE

[0001] The GLX5 is a glider, the size of an airplane. [Fig.l] "The GLX5" is used for its finesse, the many devices mentioned, which the GLX5 has, fit on an airplane.

[0002] The GLX5 in fact has, according to a first characteristic, a cleverly studied profile of the fuselage and the span of these wings which characterizes a glider [Fig.2]. The design of this one is identical to an airplane, it is characterized by the ovoid shape of the front part and a conical fuselage which decreases to the vertical tail.

[0003] The GLX5 is composed of three distinct parts, [Fig.3]; [Fig. 18] an ovoid part

[0004] which is broken down into subsets, F acts as a cradle, it connects the wings there is the engine room, and in another part just above a space dedicated to transport [Fig.4].

[0005] These parts are assembled together by fusible bolts and four hooks distributed on the platform [Fig.5] on which the second part rests.

[0006] This is the main rescue module characterized because it is an aircraft.

[0007] The cockpit constitutes the last part of this assembly, it is located in the depth which is also an aircraft (a flying wing) [Fig.3]. But this arrangement can be modular. The cockpit can be located in the ovoid part, at the front which is the most common and the aircraft located at the end of the drift can be a drone [Fig. 18], allocated to multiple other tasks that could be attributed to it, help in the geolocation of the rescue module, storage place of the black boxes.

[0008] The GLX5 is characterized by three turbojets, one of which is larger and more powerful, representing on its own a thrust equivalent to the other two combined. Its weight is a key element in the balance of the whole device, as for the other two, they are located on each side of it [Fig.4],

[0009] The drift is characterized by additional symmetrical biconvex elevators, this Alpha device [Fig.6], [Fig.7], is hidden in the vertical tail. The drift has its base of conical shape this characteristic allows the two control surfaces having the base to blend into the mass of the fuselage, it admits a hollow axis on which the two control surfaces are assembled, so that they can pivot [Fig.8], [Fig. 12] ] The base of the control surfaces are formed of two semicircles which allow the assembly on the axis of the drift [Fig.8]; [Fig. 12]; [Fig. 14][Fig. 15]. They pivot in opposite directions to each other thanks to an electric motor, they admit a deflection of 180 °.

[0010] This elevator ensures stability when disassembling the aircraft. evacuation [Fig. 18],'[Fig.31].

[0011] Located at the end of the vertical tail. This tail admits two molded metal panels of the shape of these [Fig. 16] these panels have the particularity of deforming in order to fill the space left when the elevators are out of their location, in order to guarantee a minimum of drag. This Beta device is based on one of the characteristics of the metal, its deformation when it is stressed. The device controls this deformation by transforming these panels into convex planes [Fig. 16],'[Fig. 17]. These two panels that form these prints distributed symmetrically on either side of the drift are glued on a rubber membrane which is airtight, composed inside of several parts having for each of them a difference in thickness separated by a partition. This deformation is created by injecting air inside 1,2 of these membranes.

[0012] These depth controls, [Fig.3] come in relay when the control

[0013] main, which serves as an evacuation module (flying wing) or drone, positioned At

[0014] top of the drift. [Fig.18] is no longer there, in order to ensure stability and control of the aircraft.

[0015] At the end of this drift is a horizontal plane which serves as a "landing" and a device which allows the flying wing to be gripped. [Fig. 19].

[0016] A Gamma counterweight device is located at the front of the fuselage [Fig.4] [Fig.51], it

[0017] is composed of two axes secured to the fuselage on which a counterweight slides laterally as required.

[0018] In this drift there are two airlocks, one which is outside the aircraft, in the void, the other which ensures the connection between the flying wing and the rest of the aircraft.

[0019] The GLX5 is characterized by a Delta retractable wing device [Fig.20] composed of three parts [Fig.21] (3,4,5) thus modifying its wingspan on the ground, this characteristic gives it in the event of damage, (facing a water landing), the particularity thanks to the deflections of parts (5) and (4) of 180° [Fig.24] around their respective axes of landing on a body of water.

[0020] They are characterized by two side members which run through each of its wings

[0021] [Fig.22] at the ends of which two holes are present, they allow the passage

[0022] of an axis to assemble each of the parts together, these axes are notched at their ends and are made integral with parts (5) and (4). Each of the parts which

[0023] assemble have a circular shape at their joint, which allows a rotation of

[0024] 180° around their respective axes [Fig.24]. The passage from one position to the other made by electric motors which operate a toothed wheel (6) the contact of which here on the notched axes of parts (5) and (4) allows their rotation of parts (5) and (4). The locking in horizontal position is carried out by two axes (11) present in parts (4) and (5). These axes pass through the wing section (3) in wing section number (4), the same device is located in wing section number (4) which allows the locking of part number (5). Each of the parts (4) and (5) can be controlled independently.

[0025] Principle of operation during a water landing. To limit the impact of the fuselage on a body of water, parts (4) and (5) pivot around their axes, the elevators hidden in the empennage move to the vertical position in the opposite direction after rotation is completed and those for rounding during a water landing. As soon as parts (5) are immersed in the water, they offer a slight lift this is associated with the ground effect provided by parts (3) by their speeds, this creates an air cushion, the weight carrying which has the effect of gently slowing down the impact of the fuselage on a body of water.

[0026] The GLX5 is characterized in that it has three evacuation devices

[0027] Sigma, Zeta, Omega evacuations [Fig.26] from the main cell; [Fig.27] composed of two ejection modules which are aircraft and an airlock [Fig.50] in the fuselage, independent of each other in the event of damage to the aircraft.

[0028] The first Sigma device.

[0029] The first module is located at the front of the GLX5, in the ovoid part, located at the top of it just above the engines. This part is called the canopy, it is joined to the cradle by fusible bolts and four hooks which are distributed on the platform [Fig.52] on which it rests. This aircraft is composed of; Two ailerons which are symmetrical convex shapes and which have the particularity of blending into the mass of the wings of the GLX5 [Fig.28], [Fig.29] each aileron has a rudder, an inverse V-shaped empennage located at the rear end also composed of a rudder.

[0030] An airlock located inside the canopy serves as a connection to the rest of this assembly.

[0031] This canopy is not translucent, the materials that compose it are identical to

[0032] those found on most airliners. The characteristic of this one is that it has above the Portholes a curved "TV" screen covering in the expected shape, which joined end to end, forms a dome, coupled with high definition cameras located outside, gives the illusion of having a panoramic exterior view.

[0033] The GLX5 is characterized by a Theta device hidden in the floor of this

[0034] module, this device is composed of four hollow arms of cylindrical shape [Fig.30]

[0035] (8), [Fig.31] having a cylindrical base, assembled perpendicular to the arms, on the side of this base there is a hole which allows the assembly of the elements that composes this device, this base allows the passage of an axis which connects the arm and fan assembly to the structure of the ejection module (these are the means of propulsion of the aircraft). These arms pivot on their axes (x) by means of electric motors present in their base. Inside these arms, at the end there is a device composed of a crown

[0036] notched this one is mounted on a bearing [Fig.34], the whole is integral with the arm. At the ends of these are positioned a fan [Fig.33]; [Fig.32] having the same cylindrical base but having an axis of a smaller diameter which penetrates to

[0037] the interior of this cylinder and whose end has a thread, which allows assembly

[0038] of the two elements. Around this section there are three electric motors hidden

[0039] in the cylindrical part leaving only the three pinions (9) visible [Fig.33] In these fans two axes intersect, at their junction [Fig.32], there are two electric motors

[0040] opposed symmetrically to cancel the torque of the propellers when they turn. These fans pivot around the axis (z) thanks to the three electric motors present in the junction of the fan [Fig.33] (9). The four electric motors represent the means of propulsion of this rescue module, they are supplied with electricity by batteries housed in the floor of the module [Fig.35] (10)

[0041] The main function of the Theta device is to slow down the fall of this module, when the fans are positioned horizontally (they are parachutes) in a way. They can also serve as an airbrake when the fans are in a vertical position, when this aircraft lands on a runway.

[0042] The GLX5 is characterized by an Iota device allowing it to land on any

[0043] type of terrain, including those on slopes [Fig.36], [Fig.37] it consists of six arms

[0044] articulated distributed around this module. Each arm has four joints and is composed of three parts [Fig.38] (11), [Fig.39] their deployment is done by electric jacks not shown here. The first part is connected to the box where the entire train is located, these are two metal arms have a circular shape to take out the entire device without it touching the external walls of the structure of the module, they have a rotation on the axis (x).

[0045] Parts two and three allow the deployment of the device in rotation on the axis x'x" the end of the last part is connected to a hatch (x'"), which conceals the entire device in the boxes where they are located. This hatch has another function, it serves as a "foot" these feet are characterized by their beveled shapes of each of them allowing penetration into the ground (12) to stabilize the module when it lands vertically. We find backed by this hatch a landing gear [Fig.39] composed of wheels ensuring that this aircraft can land on a runway if necessary.

[0046] The role of the Iota device is to participate in the coupling of the two parts, thanks to the hatches which are against the walls of the platform on which it rests, to absorb the impact on the ground of the aircraft but also to keep whatever the type of terrain encountered, the module level for the comfort of the passengers.

[0047] Arrangement for an airplane

[0048] The ZoZa device provides this aircraft with additional landing gear,

[0049] when the rescue module lands vertically. The Iota device is simplified

[0050] by the fact that all aircraft have landing gear and associated hatches. The Iota device is based on the existing hatches.

[0051] These are reinforced to support the weight of the device and have articulated arms

[0052] like those of the GLX5 [Fig.40] having the function of absorbing the impact on the ground,

[0053] allow landing on any type of sloping terrain, while always keeping this rescue module level.

[0054] Principle of operation of the uncoupling of the rescue module, this maneuver is executed either by the captain or by an artificial intelligence, if the latter is not there, in this case this aircraft transforms into a rescue drone. Each of the hatches where the propulsion means of this module are located are unlocked then are pushed mechanically by two cylinders in translation. As soon as there is a sufficient gap between the hatches and the edge of the module, the latter thanks to electric motors present at the joints of the cylinders, pivot horizontally [Fig.30] the Theta device comes out of its box by pivoting, the fans located at the ends of the arms pivot in the direction of the relative wind, the motors present in their fans turn.

[0055] As soon as the hooks present in the platform which hold the canopy unlock

[0056] rust, the landing gear hatches in contact with the platform help to uncouple the two parts. They exert pressure against the wall on which they rest. Under the effect of this pressure and the weight of the lower part, the fusible bolts which hold the fuselage to the canopy give way.

[0057] Arrangement on an aircraft unlike the GLX, a resource of the device

[0058] allows them to be broken.

[0059] A gap is created between the module's fins and the GLX5's main wing, providing

[0060] the rescue module's fins with its own lift, allowing it to fly.

[0061] The dual electric motors pull the module forward to move it away

[0062] of the fuselage. This aircraft can land vertically or on a runway

[0063] finally whatever the scenario and this thanks to the devices, Iota, Theta.

[0064] The second Omega evacuation device.

[0065] This module is an aircraft [Fig.41] located at the end of the drift; depending on the confi-

[0066] figure that we want this can be the cockpit, one of the main characteristics of the GLX5 or a drone [Fig.42] [Fig.53] This module is completely

[0067] autonomous, they have motors, these smaller control surfaces blend into that

[0068] used by the GLX5.

[0069] This flying wing is characterized because it combines three functions, the rudder

[0070] main depth of the GLX5, an evacuation aircraft or a drone depending on the

[0071] configuration chosen, the cockpit of the GLX5.

[0072] Arrangement on an aircraft

[0073] Here the aircraft propulsion mode is different, it is equipped with two propellers

[0074] counter-rotating to eliminate the torque effect thereof.[Fig.53]

[0075] It is characterized by a P / w device composed of eight landing gears

[0076] (smart) [Fig.44], three symmetrically opposed and two in the longitudinal axis of the wing

[0077] flying each of them has two wheels. The three landing gears are mechanically de-

[0078] pendent on their opposite twins, to grip. They are composed

[0079] of a cylindrical base having inside it a toothed crown [Fig.45] (14), of a tubular arm assembled to this base. At the opposite ends a rectangular shaped part in which is located an electric motor on which is mounted a gear [Fig.46](15), at the end of this part there are two holes which admit the passage of an axis made integral with the rectangular part. On this axis is mounted the landing gear which is composed of two parts.

[0080] A jack which has at its base, a gear [Fig.47] (16) this is assembled in the rectangular part. At the end of this, a cylindrical part, which admits a

[0081] 360° rotation thanks to an electric motor and its toothed wheel system and pinion inside it. On this cylindrical part is mounted perpendicularly, a hub on which there are two electric wheels.

[0082] Principle of operation, dropping and landing of this module. The device

[0083] ensuring the stability of the fuselage is used. [Fig.7] When dropping this aircraft

[0084] the elevator comes out of these locations by pivoting, it is positioned

[0085] horizontally ensuring the stability of the device. The undocking of the module can be done,

[0086] the device that holds the flying wing unlocked [Fig. 19]. During "landing

[0087] » the maneuver takes place in two phases. First phase, the flying wing positioned vertically above the drift, the two trains [Fig.48] located in the longitudinal axis have the function of absorbing shocks due to vertical movements linked to turbulence, the six intelligent trains opposed symmetrically, have the role of centering transversely the flying wing, the tires absorb any shocks. The articulated arms pivot on their axis until they reach the vertical parts of the drift, when the six landing gears are all in contact with them [Fig.49], the arms exert a little more pressure, to grip the empennage. As soon as the assembly is stabilized, the second phase begins.

[0088] Second phase, the electric wheels turn on themselves and allow to the

[0089] millimeter near positioning of the flying wing in the location planned so that the

[0090] Tau device [Fig. 19] of locking present in the drift takes over that- here

[0091] is composed of two jacks equipped with clamps at these ends. As soon as these are in

[0092] face of the mark, the Tau device comes out of its housing and comes to be locked at

[0093] the interior of the flying wing at the locations provided for lashing. The wheels

[0094] symmetrically opposed pivot on itself vertically while maintaining the

[0095] pressure on the drift to assist the movement of the flying wing downwards, while the landing gear located in the longitudinal axis always in contact with the drift pivot gradually to return to their boxes, as soon as the flying wing has become integral with the whole of the GLX 5, the landing gear returns to its location, as well as the elevator of the GLX5 which provided the relay.

[0096] The third Zeta evacuation device is an integral part of the fuselage, it is

[0097] located at the rear of the aircraft [Fig.50]. It consists of a hollow tube with the dimensions

[0098] of an adult, this tube is transparent, at the end of it an airlock which gives access

[0099] towards the outside. The opening of this airlock is controlled by the one who is inside.

[0100] Operating principle, an individual equipped with a parachute positions himself

[0101] inside this cylinder, which he locks behind him, he controls the opening of this

[0102] airlock, this is directly connected via a tube which crosses the

[0103] drifts, towards F outside. The opening of this airlock creates a pressure difference which

[0104] causes a suction. The individual then finds himself thrown outside.

Claims

Claims

1. Aircraft, equipped with evacuation devices, comprising three distinct parts; the first part is a cradle to which wings are connected and, above the cradle is the second part which is a space dedicated to transport, this space being an aircraft (called Sigma) which can serve as an evacuation device; the cradle and the space dedicated to transport are connected by fusible bolts and hooks, these two parts connected together form a front part and a fuselage of the aircraft; the aircraft also comprises at its rear end a vertical tail, constituting the third part and comprising a fin which has at its end a horizontal plane serving as a landing and making it possible to grip a flying wing or a drone constituting a second evacuation device (called Omega); a third evacuation device (called Zeta) is located in the rear part of the fuselage;the three evacuation devices are independent of each other.;

2. Aircraft according to claim 1 characterized in that the Sigma evacuation device comprises two symmetrical convex-shaped fins which blend into the mass of the wings of the aircraft, each fin having a rudder and an inverted V-shaped tail located at the rear end and composed of control surfaces.

3. Aircraft according to any one of the preceding claims, characterized in that it comprises two additional control surfaces assembled on two semicircles, the two semicircles merge into the fuselage and the two control surfaces are concealed in the rudder; the two control surfaces are of symmetrical biconvex shape, pivot in opposite directions and ensure the stability of the aircraft during disassembly of the Sigma evacuation device.

4. Aircraft according to any one of the preceding claims, characterized in that the Sigma evacuation device comprises a device, called Theta, composed of four hollow, deformed cylindrical arms each comprising a fan at their end, the fans are positioned horizontally in order to slow the fall of the Sigma evacuation device or vertically to serve as an airbrake when the Sigma evacuation device lands on a runway.

5. Aircraft according to the preceding claim characterized in that the front part is ovoid in shape and / or the Theta device is concealed in the floor of the Sigma evacuation device.

6. Aircraft according to any one of the preceding claims, characterized in that the Sigma evacuation device comprises a device called Iota, serving as landing gear and composed of six articulated arms distributed around the Sigma evacuation device, each arm comprising four articulations and being composed of three parts.

7. Aircraft according to any one of the preceding claims characterized in that the second Omega evacuation device has motors and these smaller control surfaces merge into those of the aircraft, Omega also comprises a device, called Phi, composed of eight landing gears, three symmetrically opposed and two in the longitudinal axis of Omega, each landing gear having two wheels, the three landing gears are mechanically dependent on their opposite twin, to grip, they are composed of a cylindrical base having inside it a toothed crown, a tubular arm assembled to this base; at the opposite ends, a rectangular deformed part in which there is an electric motor equipped with a gear (15), at the end of this part there are two holes which admit the passage of an axis;on this axis is mounted a landing gear which is composed of two parts: a jack which has, at its base, a gear (16), the jack is assembled in the rectangular part; a cylindrical part, which admits a rotation at 360° thanks to an electric motor and its system of toothed wheel and pinion inside it, on this cylindrical part is mounted perpendicularly, a hub on which there are two electric wheels.;

8. Aircraft according to any one of the preceding claims, characterized in that the cockpit is located in the front part or in the second evacuation device (Omega) Omega.

9. Aircraft according to any one of the preceding claims, characterized in that the wings are retractable wings composed of three parts (3, 4, 5) thus modifying the ground span of the aircraft and allowing it to land on a body of water thanks to the 180° movements of the parts (5) and (4) around their

10. respective axes, the wings are traversed by two spars at the ends of which two holes allow the passage of an axis to assemble each of the parts together, these axes are notched at their ends and are made integral with the parts (5) and (4), each of the parts which are assembled have a circular shape at their joint, which allows a rotation of 180 ° around their respective axes, the passage from one position to the other is done by electric motors which actuate a notched wheel (6), the contact of this one on the notched axes of the parts (5) and (4) allows the rotation of the parts (5) and (4), the locking in horizontal position is carried out by two axes (11) present in the parts (4) and (5), these axes pass through the part (3) and the part (4), the same device is in the part (4) which allows the locking of the part (5), each of the parts (4) and (5) can be controlled independently. Aircraft according to any one of the preceding claims, characterized in that the cradle comprises engines and / or the drift comprises a Tau device making it possible to lock the flying wing to the drift.

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