• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The present invention relates to an aircraft (1) provided with a cell (2) which delimits at least one internal space (11) extending in elevation and from bottom to top of a floor (16) towards a ceiling (17) , said aircraft comprising a buoyancy system (20), the buoyancy system (20) being provided with at least two outer floats (30) arranged transversely on either side of an anteroposterior plane (100) to the outside (EXT) of the cell (2). The buoyancy system (20) has at least one inner float (35) arranged in an inner space (11), each inner float (35) being disposed above a plane (200) which is perpendicular to the anteroposterior plane (100). ) and which passes through two outer floats (30) disposed on either side of the cell (2).
    公开号:FR3043061A1
    申请号:FR1502308
    申请日:2015-11-02
    公开日:2017-05-05
    发明作者:Jean Jacques Ferrier
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    Aircraft with buoyancy system and method of buoyancy
    The present invention relates to an aircraft equipped with a buoyancy system, as well as a buoyancy method. Therefore, the invention lies in the technical field of buoyancy systems for landing and stability afloat of an aircraft, and more particularly a rotary wing aircraft.
    Such a buoyancy system contributes to the floatation and stability of an aircraft following a landing. The buoyancy system can be used for example following a ditching, to allow evacuation of the occupants of this aircraft. All devices dedicated to passenger missions in maritime areas are equipped in principle with such a buoyancy system.
    Certification regulations also specify that an aircraft must be able to land and be stable on the water with its buoyancy system. Stability must be proven for water-free surface conditions and wind levels that are defined in these certification regulations.
    These water-free surface states are also called "sea state", and apply to any liquid surface. The term "landing" also covers the landing of an aircraft on any water-free surface, whether on the sea or on a lake, for example. Certification regulations require the stability of an aircraft with a particular sea state.
    A buoyancy system may include floats.
    The floats are fixed on either side of a cell of the aircraft. The term "cell" refers to a portion of the aircraft housing a cockpit, or even a cabin and a cargo hold.
    For example, floats are attached to a landing gear carrying the cell, or to a wall of the cell.
    Some flotation systems include inflatable floats whose deployment is controlled either by the pilot and / or co-pilot, for example, or by an automatic trigger including through one or more sensors (s) immersion. These floats may comprise bags inflated by a deployment means.
    In addition, the floats can be paired to optimize the stability of the aircraft on the water. Therefore, the floats of a pair can be arranged on either side of the cell of the aircraft.
    US 2013/0327890 discloses an aircraft provided with multiple floats.
    A known helicopter is also provided with a flotation system comprising two pairs of floats, each float being connected to the cell by ropes. Floats are inflated inflatable floats before landing by implementing nitrogen bottles.
    Such a flotation system is satisfactory to ensure the stability of the aircraft with a level 4 sea state in particular.
    However, in an extremely turbulent sea with a sea state that is much higher than the sea state required by certification regulations or under a high intensity wave, floats may sink under the liquid surface when the aircraft has a very important roll angle.
    If the center of gravity of the aircraft is no longer at a space separating two floats of a pair of floats, the aircraft can capsize.
    To limit the risk of capsizing, the floats can be connected to a cell by an elastic means. Document US 2015/0217862 discloses an aircraft of this type.
    Furthermore, the document FR 2959725 discloses a control method for controlling an aircraft buoyancy system comprising manual triggering means and automatic triggering means of said buoyancy system. This method consists in taking into account at least one attitude parameter of the aircraft for controlling the automatic triggering means.
    The present invention therefore aims to provide an aircraft with optimized stability following a landing. The invention thus has an aircraft provided with a cell which extends longitudinally along an anteroposterior plane, this cell extending transversely from a left flank to a right flank and in elevation from a lower portion to a lower one. the top part.
    For example, the upper part and the lower part have a substantially equivalent maximum height.
    The cell defines at least one internal space extending in elevation and from bottom to top of a floor to a ceiling. The aircraft comprises a buoyancy system, the buoyancy system being provided with at least two floats known as "external floats" arranged outside the cell, two distinct external floats being arranged transversely on both sides of the plane. anteroposterior.
    In addition, the buoyancy system has at least one float called "inner float" arranged in an internal space called "buoyancy space". Each inner float is disposed above a transverse plane which is perpendicular to the anteroposterior plane and which passes through two outer floats arranged on either side of the cell. Each inner float is for example carried by a support arranged in the upper part, such as a ceiling. The expression "running through" means that the external floats concerned are intersected by the transverse plane.
    The transverse plane can pass through the center of gravity of at least one outer float. The term "buoyancy space" refers to a portion of the internal space accommodating an interior float.
    Therefore, the aircraft includes floats arranged outside the cell. These floats are referred to as "outdoor floats" for convenience because of their location.
    In addition, the aircraft comprises at least one float disposed inside the cell. Each float of this type is called "inner float" for convenience because of its location.
    As a result, the aircraft comprises at least two external floats arranged on either side of the cell, and an inner float disposed in the cell.
    In addition, each inner float is disposed above a transverse plane passing through the outer floats, when the aircraft has a zero roll angle. For example, the outer floats are arranged at the bottom of the cell and in particular substantially at the floor of an internal space, while each inner float is by construction in the upper part. Then in a cross section, two outer floats and an inner float represent approximately the vertices of a triangle. For example, the centers of gravity of two outer floats and an inner float represent the vertices of a triangle.
    As a result, if the aircraft turns over because of a particularly severe sea state or a particularly violent wave, an outside float is located outside the water. On the other hand, another external float and the inner float can keep the aircraft afloat, by providing a non-submerged zone in the aircraft.
    In addition, the arrangement of an inner float in the cell has the advantage of protecting the inner float during landing. This inner float is protected within the cell which tends to reduce the risk of damage to the inner float during the impact of the aircraft with water.
    In addition, if an outer float is degraded, this inner float can then possibly overcome the accidental breakage of an outer float. The aircraft may further include one or more of the following features
    Thus, each inner float may extend longitudinally over a maximum length as well as transversely over a maximum width and in elevation over a maximum height, said maximum length being greater than the maximum height, said maximum length being greater than the maximum width.
    As a result, the inner float extends longitudinally in the buoyancy space.
    In addition, a buoyancy space extending longitudinally over a total length, an inner float can extend longitudinally over a maximum length equal to this total length.
    The inner float then extends longitudinally over the entire length of the buoyancy space.
    In addition, at least one interior float can be suspended from a ceiling.
    This characteristic makes it possible to position the float in the upper part of the cell.
    In another aspect, a buoyancy space is to be chosen from a list comprising a cabin as well as a cockpit and a cargo hold.
    The term "cockpit" refers to a section of the airframe in which the pilot and flight instruments of the aircraft are located. The term "cabin" refers to a section of the cell in which passengers are. The term "hold" refers to a section of the cell in which there is cargo, such as luggage for example.
    Thus, a cabin and / or a hold and / or a cockpit can each accommodate at least one interior float.
    Furthermore, a buoyancy space comprising a corridor disposed between two rows of seats, at least one inner float is arranged above this corridor.
    In particular, the cabin of the aircraft may comprise a central corridor. At least one interior float can then be housed above this corridor, between two ceiling cladding for example.
    This arrangement is to facilitate the evacuation of passengers by not positioning the inner floats above the head of the passengers.
    In addition, at least one of the floats can be inflatable, the buoyancy system being provided with an inflation system for inflating each inflatable float, the buoyancy system having a control system for giving an inflation order of each inflatable float to inflation system.
    For example, each float is inflatable.
    The inflation system may comprise one or more electric, chemical, pyrotechnic, pneumatic inflators. Each inflator is then connected to at least one float.
    The control system may comprise manual activation means of the button type, or even calculators determining if inflation conditions are met. For example, a computer is connected to at least one immersion sensor for detecting whether the aircraft has landed, and / or at least one button for detecting whether a pilot requires the inflation of at least one float. The use of inflatable floats optimizes the operation of the aircraft by not inflating the floats when these floats are not useful.
    When at least one outer float and at least one inner float are inflatable, the control system may include an external control device dedicated to inflating each inflatable outer float and an inner control device dedicated to inflating each inflatable inner float.
    The inner floats can be inflated independently of the outer floats.
    For example, outdoor floats are systematically inflated if a landing occurs. On the other hand, the inner floats can be inflated only during a reversal so as not to hinder the evacuation of the occupants of the aircraft in the absence of reversal.
    When at least one inner float is inflatable, the inner control device may comprise measuring means which measures a roll angle of the aircraft, the inner control device having a processing unit connected to the measuring means for inflating each inflatable inner float when the aircraft reaches a roll angle greater than or equal to a threshold.
    Thus, the processing unit may comprise a processor or equivalent. The measuring means may have an inclinometer or an inertial unit comprising at least three gyrometers and at least three accelerometers. The processing unit is further connected to at least one inflator in communication with inner floats.
    On the other hand, the external control device may include members to determine whether a landing will occur or whether a landing has occurred. According to the previous example, the external control device comprises at least one immersion sensor capable of generating a control signal transmitted to at least one inflator in communication with external floats. Therefore, following a landing, at least one immersion sensor detects the presence of water, and induces the inflating of the outer floats.
    In parallel, the processing unit determines whether the current roll angle reaches a threshold, and if so, controls the inflation system to inflate the inner floats. This threshold is determined by the manufacturer according to the position of the floats in particular.
    Furthermore, the buoyancy system may comprise at least one seat having a sealed volume at least partially filled with gas.
    For example, a sealed volume is provided under a seating of a seat or in foam seat upholstery. Each sealed volume can participate in maintaining the aircraft afloat.
    In addition to an aircraft, the invention relates to a buoyancy method for floating an aircraft provided with a cell that extends longitudinally along an anteroposterior plane, the cell extending transversely from a left flank to a right flank and in elevation from a lower portion to an upper portion, the cell defining at least one internal space extending in elevation from a floor to a ceiling, the aircraft comprising a buoyancy system, the buoyancy system being provided with two floats called "external floats" arranged outside the cell, two separate external floats being arranged transversely on either side of the anteroposterior plane outside the cell.
    This method comprises a step of disposing at least one so-called "inner float" float in an internal space called "buoyancy space", each inner float being disposed above a transverse plane which is perpendicular to the anteroposterior plane and which passes through two external floats arranged on both sides of the cell.
    Optionally, each outer float is inflated following a landing, at least one inner float being inflated only when the aircraft reaches a roll angle greater than or equal to a threshold.
    According to another variant, all the floats are inflated at the same time, before or after landing by applying conventional methods. The invention and its advantages will appear in more detail in the following description with examples given by way of illustration with reference to the appended figures which represent: FIG. 1, a diagram showing an aircraft equipped with a floatability according to the invention, - Figure 2, a schematic cross section of this aircraft, - Figure 3, a schematic longitudinal section of this aircraft, and - Figures 4 to 7, diagrams explaining the operation of the invention.
    Note that three directions X, Y and Z orthogonal to each other are shown in the figures.
    The first direction X is called longitudinal. The term "longitudinal" relates to any direction parallel to the first direction X.
    The second direction Y is called transverse. The term "transverse" is relative to any direction parallel to the second direction Y.
    Finally, the third direction Z is said in elevation. The expression "in elevation" relates to any direction parallel to the third direction Z.
    FIG. 1 shows an aircraft 1 equipped with a buoyancy system 20 according to the invention. This aircraft can notably be a rotorcraft.
    This aircraft 1 comprises a cell 2 extending longitudinally from a front end 3 to a rear end 4 along an anteroposterior plane 100. In addition, the cell 2 extends transversely from a left flank 5 to a sidewall right 6 on either side of the anteroposterior plane 100, and in elevation from a lower portion 7 to an upper portion 8. Optionally, the anteroposterior plane is a plane of symmetry of the aircraft.
    The lower part has a bottom of the cell while the upper part has the top of the cell. The lower part is conventionally equipped with a landing gear, while the upper part can carry a rotor 9 participating in the lift or propulsion of the aircraft. The lower part may include a boat bounded in particular by the floor of an internal space and the outer casing of the cell.
    The upper part can therefore carry a rotor 9 in the context of a rotorcraft. This rotor 9 is rotated by at least one motor 110 through a power transmission box 120. This engine 110 may be a turbine engine equipped with an expansion turbine secured to a working shaft, the shaft working piece being connected by a mechanical chain to the power transmission box 120.
    The lower part can then represent the lower half of the cell while the upper part represents the upper half of this cell.
    Furthermore, the interior INT of the cell 2 has internal hollow spaces 11 which are delimited by the outer envelope and various partitions. Each internal space 11 then represents a compartment which extends in particular in elevation of a base called "floor" for convenience to a ceiling. Optionally, the ceiling of one compartment may represent the floor of another compartment.
    In addition, this aircraft 1 is further provided with a buoyancy system 20 according to the invention to be able to fish.
    Such a buoyancy system 20 is provided with at least three floats 25. Each float may comprise an envelope that floats on the water, this envelope trapping a gas for example.
    In particular, the buoyancy system 20 is provided with at least two floats 25 called "external floats 30" arranged on either side of the cell 2 of the aircraft. Each outer float 30 is disposed outside EXT of the cell 2. The expression "disposed outside the EXT of the cell 2" means that the floats are at least partially deployed outside the cell 2 following a landing. .
    The outer floats 30 may be fixed in the usual manner to the cell 2 and / or to a landing gear for example. These external floats may be structural floats or inflatable floats.
    Thus, an outer float 30 called "left outer float 31" is disposed on the side of the left side 5 of the aircraft, while an outer float 30 called "right outer float 32" is disposed on the side of the right side 6 of the 'aircraft.
    The outer floats 30 can be matched. Therefore, the outer floats 30 of a pair can be arranged symmetrically on either side of the plane anteroposterior plane 100 of symmetry of the aircraft in a stable position of the aircraft.
    For example, the aircraft has one or two pairs of outer floats 30.
    At least one pair of outer floats 30 may be provided at the lower portion 7 of the cell. Therefore, each outer float is intersected by a transverse plane 200 perpendicular to the anteroposterior plane. The anteroposterior plane 100 can be described as a vertical plane because of its inclination substantially according to gravity when the aircraft has a zero attitude, the transverse plane 200 can be described as a horizontal plane.
    For example, each outer float 30 is positioned near the boat of an aircraft to keep the aircraft afloat.
    Referring to Figure 2, the buoyancy system 20 further comprises less a float 25 called "inner float 35".
    Each inner float 35 is arranged inside INT of the cell 2, as opposed to the outer floats which are outside the cell.
    Thus, each inner float 35 is disposed in an internal space 11 called "buoyancy space 18" for convenience. Each inner float 35 is carried by a support of this buoyancy space 18, for example by being suspended from a ceiling 17 of this buoyancy space 18 or even being arranged below this ceiling. Regardless of the variant, the inner float is arranged in the upper part of the aircraft.
    As a result, each inner float 35 is arranged at the upper part 8 of the cell, unlike the external floats which are at the lower part 7 of the cell 2. When the attitude of the aircraft is zero, each inner float 35 is thus disposed above the horizontal transverse plane 200 which is perpendicular to the anteroposterior plane 100 and which passes through two outer floats 30 disposed on either side of the cell 2. The center of gravity of at least one float For example, the outer center of gravity of an inner float is present in an upper plane perpendicular to the anteroposterior plane 100. This upper plane overhangs the center of gravity of each outer float when the attitude of the aircraft is zero, namely when the roll angle and the pitch angle of the aircraft are damaged.
    In addition, a buoyancy space 18 may comprise a central corridor 40 transversely separating two rows 42, 43 of seats 41. A ceiling covering 80 usually overhangs each row 42, 43 of seats 41. Such a ceiling covering 80 may comprise Storage lockers 81, lighting means 82, air conditioning vents 83 ... Therefore, at least one inner float 35 can be positioned between the ceiling cladding 80, and therefore above the corridor 40. The expression "Above the corridor 40" means that the inner float 35 overhangs the floor 16 partially delimiting in elevation the corridor.
    Moreover, at least one inner float 35 may be inflatable. Therefore, at least one outer float 30 and / or at least one inner float 35 are inflatable. Optionally, all the floats 25 are inflatable. As a result, the inflatable floats are deflated outside the landing phases. The inflatable floats can in particular be folded into an envelope provided for this purpose.
    Under these conditions, the buoyancy system includes an inflation system 50 for inflating each inflatable float. This inflation system 50 comprises at least one inflator 51 for inflating the inflatable floats. Each inflator can include an electric, explosive, pneumatic or chemical inflator ...
    For example, but not exclusively, an inflator 51 is connected to a plurality of floats 25. FIG. 2 illustrates inversely an inflation system 50 comprising several inflators 51. By way of illustration, the inflating system 50 may comprise at least one inflator 51 dedicated to the outer floats 30 and at least one inflator 51 dedicated to the inner floats 35. Optionally, the inflation system comprises at least one inflator 51 per float.
    We can refer to the state of the art to find examples of embodiments of the inflator floats and inflation systems of these floats.
    In addition, the buoyancy system is provided with at least one control system 55 for controlling the inflators 51. This control system 55 is then connected to at least one inflator 51 to require inflation of the floats 25.
    The control system 55 may be a conventional system.
    This control system may, however, comprise a computer having for example a processor, an integrated circuit, a programmable system, a logic circuit, these examples not limiting the scope given to the term "calculator".
    This calculator can be optionally armed by activation means 70 operable by an individual. The activation means may have at least one position to make the buoyancy system active. Thus, the buoyancy system can be inhibited in certain situations, for example when the aircraft does not fly over a liquid surface.
    The calculator can determine whether predetermined inflation conditions are fulfilled, and can activate the inflators 51 if necessary. For example, a selection means that can be controlled by an individual makes it possible to transmit to the computer an inflating order of the outer and / or inner floats. . The expression "means of selection" can designate a button, a touch screen, a voice control means, a keyboard or a pointer making it possible to manipulate computer means ...
    Similarly, at least one immersion sensor can detect the presence of water, and if necessary transmit to the computer an inflating order of the outer and / or inner floats.
    In one embodiment, the control system 55 may include an external control device 65 dedicated to inflating each inflatable outer float and an inner control device 60 dedicated to inflating each inflatable inner float.
    For example, the external control device 65 comprises at least one immersion sensor 66 and / or a selection means 67 that can be controlled by an individual or even a calculation unit that determines whether a landing has occurred for example as a function of data from navigation.
    In one example, each immersion sensor 66 and the selection means 67 and an inertial unit are connected to a computer, this computer being connected to each inflator.
    In addition, the internal control device 60 may comprise a measurement means 61 which measures a roll angle ROL of the aircraft 1. This measurement means 61 communicates with a processing unit 62 which transmits a signal to the inflators 51 to inflate. each inflatable inner float 35 when the aircraft 1 reaches a roll angle greater than or equal to a threshold. The processing unit may for example have a processor, an integrated circuit, a programmable system, a logic circuit, these examples not limiting the scope given to the term "processing unit". The processing unit and the aforementioned calculator can represent a single electronic unit. Such an electronic unit may comprise at least one processor or equivalent and a memory, code segments stored in the memory belonging to the processing unit and code segments stored in the memory belonging to the computer.
    In this context, the external control device 65 and the internal control device 60 are possibly independent, the inflation of the inner floats not necessarily required when inflating the outer floats is required.
    Furthermore, each inner float extends transversely over a maximum width 36 and in elevation over a maximum height 37.
    The term "maximum" allows to designate the largest dimension of a float in a given direction. On a circular shape of the type of Figure 2, the maximum width 36 and the maximum height 37 then represent diameters.
    With reference to FIG. 3, an inner float furthermore extends longitudinally over a maximum length 38. Optionally, the maximum length 38 is then greater than the maximum height 37, this maximum length 38 also being greater than the maximum width 36.
    In addition, a buoyancy space 18 extending longitudinally over a total length 19, an inner float 35 may extend longitudinally over a maximum length 38 equal to this total length 19.
    Furthermore, the cell may comprise various internal spaces, such as a cockpit 12, a cabin 13, a hold 14, a motor compartment 15. According to the illustration of Figure 3, the ceiling of the cabin 13 and the compartment 14 represents the mechanical floor of the engine compartment 15. This configuration is given for illustrative purposes, other arrangements being possible. Therefore, the cabin 13 and the cockpit 12 and the hold 14 can each represent a buoyancy space 18 equipped with at least one inner float 30 to the ceiling.
    According to the example of Figure 3, a cabin 13 represents a buoyancy space 18 comprising at least one inner float extending over the entire length of this cabin. The cockpit is also equipped with such an inner float. By cons, the cargo holds at least two inner floats arranged one behind the other or transversely next to each other.
    The inner floats can be arranged longitudinally one behind the other.
    In addition, the buoyancy system may comprise complementary flotation devices.
    Thus, at least one seat 43 may have a sealed volume 45 at least partially filled with gas.
    Figures 4 to 7 illustrate the method implemented by the invention.
    With reference to FIG. 4, when an aircraft 1 lands on a liquid surface 300, the outer floats 30 are deployed to at least partially ensure that the aircraft 1 is afloat.
    In the context of inflatable floats, the outer floats can be inflated in flight prior to landing, or after landing.
    On the other hand, the inner floats 35 can be deflated so as not to hinder the movement of people whereas these inner floats are not necessary for the aircraft to float.
    If the sea is rough and with reference to Figure 5, the aircraft can bow with a roll angle ROL.
    As long as this roll angle ROL is below a threshold, the inner floats are deflated. Conversely, the inner floats are inflated if the roll angle ROL reaches a predetermined threshold.
    With reference to FIG. 6, if the center of gravity CDG of the aircraft no longer overhangs the inter-float space 400 present between two external floats of a pair of floats, the aircraft 1 can turn over according to the arrow F1 .
    With reference to FIG. 7, at least one outer float 30 is then out of the water. According to the example of Figure 7, all the outer floats 32 located to the right of the cell are out of the water.
    On the other hand, the outer floats 31 located on the left of the cell and the inner floats 35 float. As a result, a first zone Z1 of an internal space may be under water, but the inner floats maintain a second zone Z2 of an internal space out of the water.
    According to another variant, the inner floats and the outer floats are all inflated in case of landing.
    Naturally, the present invention is subject to many variations as to its implementation. Although several embodiments have been described, it is well understood that it is not conceivable to exhaustively identify all the possible modes. It is of course conceivable to replace a means described by equivalent means without departing from the scope of the present invention.
    权利要求:
    Claims (15)
    [1" id="c-fr-0001]
    An aircraft (1) having a cell (2) extending longitudinally along an anteroposterior plane (100), said cell (2) extending transversely from a left flank (5) to a flank right (6) and in elevation from a lower part (7) to an upper part (8), said cell (2) delimiting at least one internal space (11) extending in elevation and from bottom to top of a floor (16) to a ceiling (17), said aircraft comprising a buoyancy system (20), the buoyancy system (20) being provided with at least two floats (25) called "outer floats (30)" arranged at the outside (EXT) of the cell (2), two separate outer floats (30) being arranged transversely on either side of said anteroposterior plane (100), characterized in that said buoyancy system (20) has at least one float (25) said "inner float (35)" arranged in an internal space (11) said "space of buoyancy (18) ", each inner float (35) being disposed above a transverse plane (200) which is perpendicular to the anteroposterior plane (100) and which passes through two outer floats (30) arranged on either side of the cell (2).
    [2" id="c-fr-0002]
    2. Aircraft according to claim 1, characterized in that at least one inner float (35) is carried by a support arranged in said upper part.
    [3" id="c-fr-0003]
    3. Aircraft according to claim 2, characterized in that a support is a ceiling (17) of a buoyancy space.
    [4" id="c-fr-0004]
    4. Aircraft according to any one of claims 1 to 3, characterized in that each inner float (35) extends longitudinally over a maximum length (38) as well as transversely over a maximum width (36) and in elevation on a maximum height (37), said maximum length (38) being greater than the maximum height (37), said maximum length (38) being greater than the maximum width (36).
    [5" id="c-fr-0005]
    5. Aircraft according to any one of claims 1 to 4, characterized in that a buoyancy space (18) extending longitudinally over a total length (19), an inner float (35) extends longitudinally on a maximum length (38) equal to this total length (19).
    [6" id="c-fr-0006]
    6. Aircraft according to claim 3, characterized in that at least one inner float (35) is suspended from a ceiling (17).
    [7" id="c-fr-0007]
    7. Aircraft according to any one of claims 1 to 6, characterized in that a buoyancy space (18) is to be chosen from a list comprising a cabin (13) and a cockpit (12) and a hold (14).
    [8" id="c-fr-0008]
    8. Aircraft according to any one of claims 1 to 7, characterized in that a buoyancy space (18) comprising a corridor (40) arranged between two rows (41, 42) of seats (43), at least one inner float (35) is arranged above this corridor (40).
    [9" id="c-fr-0009]
    9. Aircraft according to any one of claims 1 to 8, characterized in that at least one of said floats (25) is inflatable, the buoyancy system (20) having an inflation system (50) for inflating each float ( 25), said buoyancy system (20) having a control system (55) for providing an inflation command of each inflatable float (25) to the inflation system (50).
    [10" id="c-fr-0010]
    10. Aircraft according to claim 9, characterized in that each float (25) is inflatable.
    [11" id="c-fr-0011]
    11. Aircraft according to any one of claims 9 to 10, characterized in that, at least one outer float (30) and at least one inner float (35) being inflatable, said control system (55) comprises a device external control (65) for inflating each inflatable outer float (30) and an inner control device (60) for inflating each inflatable inner float (35).
    [12" id="c-fr-0012]
    Aircraft according to claim 11, characterized in that, at least one inner float (35) being inflatable, said inner control device (60) comprises measuring means (61) which measures a roll angle (ROL) of the aircraft (1), said inner control device (60) having a processing unit (62) connected to the measuring means (61) for inflating each inflatable inner float (35) when the aircraft (1) reaches an angle roll (ROL) greater than or equal to a threshold.
    [13" id="c-fr-0013]
    13. Aircraft according to any one of claims 1 to 12, characterized in that said buoyancy system (20) comprises at least one seat (43) having a sealed volume (45) at least partially filled with gas.
    [14" id="c-fr-0014]
    14. Flotation method for floating an aircraft (1) provided with a cell (2) extending longitudinally along an anteroposterior plane (100), said cell (2) extending transversely of a flank left (5) to a right side (6) and in elevation from a lower part (7) to an upper part (8), said cell (2) delimiting at least one internal space (11) extending in elevation d a floor (16) to a ceiling (17), said aircraft (1) comprising a buoyancy system (20), the buoyancy system (20) being provided with two floats (25) called "outer floats (30)" arranged outside (EXT) of the cell (2), two separate outer floats (30) being arranged transversely on either side of said anteroposterior plane (100) outside (EXT) of the cell (2) , characterized in that there is at least one float (25) called "inner float (35)" in a space i internal (11) said "buoyancy space (18)", each inner float (35) being disposed above a transverse plane (200) which is perpendicular to the anteroposterior plane (100) and which passes through two outer floats (30) arranged on either side of the cell (2).
    [15" id="c-fr-0015]
    15. The method of claim 14, characterized in that each outer float (30) is inflated following a landing, at least one inner float (35) being inflated only when the aircraft (1) reaches a roll angle (ROL ) greater than or equal to a threshold.
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    EP3718884A1|2020-10-07|Aircraft provided with a flotation system, and flotation method
    KR20110012040U|2011-12-30|Ship having expansion tube for compensating buoyancy
    KR101732508B1|2017-05-04|Ships
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    同族专利:
    公开号 | 公开日
    EP3162712A1|2017-05-03|
    FR3043061B1|2017-10-27|
    EP3162712B1|2018-01-03|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    JPH08192797A|1995-01-19|1996-07-30|Ayako Otsuka|Safety helicopter|
    CA2190783A1|1996-11-20|1998-05-20|Henry Shooflar|Aircraft and passenger survivability apparatus and method|
    US20050077426A1|2003-10-08|2005-04-14|Martin Simard|Flotation device for small airplanes|
    US20150217862A1|2014-01-31|2015-08-06|Airbus Helicopters|Buoyancy system for an aircraft, and an aircraft|EP3409585A1|2017-06-02|2018-12-05|Airbus Helicopters|An aircraft provided with a buoyancy system, and a buoyancy method|US5669980A|1995-03-24|1997-09-23|Atotech Usa, Inc.|Aluminum desmut composition and process|
    FR2959725B1|2010-05-04|2013-10-25|Eurocopter France|METHOD FOR CONTROLLING AN AIRCRAFT FLOATING SYSTEM AND CONTROL SYSTEM USING THE SAME|
    EP2678220B1|2011-02-25|2017-10-11|Archimedes Pty Ltd|Buoyancy system|FR3069526B1|2017-07-27|2021-02-26|Airbus Sas|PASSIVE SAFETY DEVICE WITH AIRBAGS AND AIRCRAFT EQUIPPED WITH SUCH A DEVICE|
    CN108100242B|2017-12-03|2018-12-11|中国直升机设计研究所|A kind of external helicopter short limb floating drum cabin|
    FR3094691B1|2019-04-04|2021-02-26|Airbus Helicopters|Aircraft equipped with a buoyancy system, and buoyancy method|
    法律状态:
    2016-11-18| PLFP| Fee payment|Year of fee payment: 2 |
    2017-05-05| PLSC| Search report ready|Effective date: 20170505 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-11-23| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-16| ST| Notification of lapse|Effective date: 20200906 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1502308A|FR3043061B1|2015-11-02|2015-11-02|AIRCRAFT HAVING A FLOATABILITY SYSTEM, AND FLOATABILITY METHOD|FR1502308A| FR3043061B1|2015-11-02|2015-11-02|AIRCRAFT HAVING A FLOATABILITY SYSTEM, AND FLOATABILITY METHOD|
    EP16192159.8A| EP3162712B1|2015-11-02|2016-10-04|Aircraft provided with a floatation system, and floatation method|
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