• 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 invention relates to a crocodile rudder comprising: - an upper flap, - a lower flap, - an actuating mechanism which ensures the rotational displacement of each flap around a common axis (20) in the same direction, or in different directions, and - a locking mechanism (220) alternately taking a locking position in which the upper flap and the lower flap are fixed relative to each other and an unlocking position in which the upper flap and the lower flap are free relative to each other. Such a crocodile ruler is thus stiffened by the locking mechanism that secures the two flaps.
    公开号:FR3053956A1
    申请号:FR1656831
    申请日:2016-07-18
    公开日:2018-01-19
    发明作者:Jerome Robillard；Pierre DOUREL
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    TECHNICAL AREA
    The present invention relates to a crocodile type control surface for an aircraft, as well as to an aircraft comprising such a crocodile control surface, as well as to a method for adjusting such a crocodile control surface.
    STATE OF THE PRIOR ART
    A prior art aircraft has a number of control surfaces which allow control of certain axes of the aircraft. In particular, an aircraft comprises at least one control surface of the crocodile type, that is to say a control surface comprising two flaps each being mounted to be movable in rotation. The two flaps are arranged one against the other, and each is controlled in rotation by an actuator. The two flaps can thus be controlled independently of one another, either in the same direction of rotation, or in opposite directions to move away from each other and then having a shape identical to an open mouth of a crocodile.
    When the two flaps are moved in the same direction, they behave like a monobloc spoiler or a rudder, and when the two flaps are moved in opposite directions, they behave like an airbrake.
    Currently, the rigidity of such a crocodile type control surface is ensured by the internal rigidity of each flap, which requires the installation of heavy flaps.
    STATEMENT OF THE INVENTION
    An object of the present invention is to provide a crocodile type control surface which is stiffened by a locking mechanism which makes it possible to reduce the structure of each flap.
    To this end, a crocodile control surface is proposed comprising:
    - an upper flap,
    - a lower flap,
    - an actuation mechanism which ensures the rotational movement of each flap around a common axis either in the same direction or in different directions, and
    a locking mechanism alternately taking a locking position in which the upper flap and the lower flap are fixed relative to one another and an unlocking position in which the upper flap and the lower flap are free one by compared to each other.
    Such a crocodile control surface is thus stiffened by the locking mechanism which secures the two flaps.
    Advantageously, the actuation mechanism includes:
    - a first actuator,
    - a second actuator,
    an upper connecting rod fixed by one end to the upper flap and by another end to the first actuator, and
    a lower connecting rod fixed by one end to the lower flap and by another end to the second actuator, the upper connecting rod and the lower connecting rod being mounted so as to be able to rotate about the common tax.
    Advantageously, one of the connecting rods has a first shaft while the other connecting rod has a second shaft which is hollow and in which said first shaft is housed, the locking mechanism comprises:
    - a jack whose cylinder extends the second shaft and whose piston extends the first shaft, defining a chamber between the bottom of the cylinder and the piston,
    an energy source connected to the chamber and adapted to alternately take a pressurized position in which it pressurizes the chamber and tends to push the piston from the bottom of the chamber, and a pressureless position in which it does not put not the pressure chamber,
    - a return means which forces the piston to approach towards the bottom of the chamber, and part of the internal surface of the cylinder takes the form of a first truncated cone and part of the external surface of the piston takes the form a second truncated cone, the two truncated cones being arranged so that in the unpressurized position, corresponding to the locking position, their lateral surfaces are in contact preventing any movement of one relative to the other, and so that in the pressurized position, corresponding to the unlocking position, their lateral surfaces are not in contact allowing movements of one relative to the other.
    The invention also provides an aircraft comprising a structure and at least one crocodile control surface according to one of the preceding variants fixed to said structure.
    The invention also provides a method for controlling a crocodile control surface according to one of the preceding variants, said control method comprising:
    - a displacement step during which the actuation mechanism displaces the two flaps to an angular position,
    - when the flaps have reached said angular position, an overload step during which the actuation mechanism applies to each flap a force corresponding to an angular difference tending to bring them together and previously evaluated during an adjustment step.
    Advantageously, said adjustment step comprising:
    - a clamping substep during which a first flap is clamped to a reference angular position,
    - an application sub-step during which a force is applied to the second flap, said force tending to press the second flap against the first flap,
    - an evaluation sub-step during which the angular deviation of the second component and corresponding to the force thus applied is evaluated,
    - a clamping sub-step during which the second flap is clamped to the angular reference position,
    - an application sub-step during which a force is applied to the first flap, said force tending to press the first flap against the second flap,
    - an evaluation sub-step during which the angular deviation of the first component and corresponding to the force thus applied is evaluated.
    BRIEF DESCRIPTION OF THE DRAWINGS
    The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in relation to the accompanying drawings, among which:
    Fig. 1 shows a top view of an aircraft comprising a control surface according to the invention, FIG. 2 shows a rear view in section of the control surface according to line II-II of FIG. 1, FIG. 3 shows a side view in section of the control surface according to line III-III of FIG. 1, FIG. 4 shows a section through a locking mechanism, FIG. 5 shows a position for adjusting the control surface horizontally, and FIG. 6 shows a tilted position of the control surface.
    DETAILED DESCRIPTION OF EMBODIMENTS
    In the following description, the control surface is a fin of a wing, but the invention applies in the same way to the other control surfaces of the aircraft such as the elevator, the rudder, or the like, as long as that the control surface can be used as an air brake.
    Fig. 1 shows an aircraft 100 comprising a fuselage 102 and two wings 104ab fixed on either side of the fuselage 102. Each wing 104a-b carries a number of fins, at least one of which constitutes a crocodile control surface 150.
    Fig. 2 and FIG. 3 show the crocodile control surface 150 in section. The crocodile control surface 150 comprises an upper flap 152 and a lower flap 154.
    The crocodile control surface 150 also includes an actuation mechanism 210 which ensures the rotational movement of each flap 152, 154 around a common axis 20 either in the same direction of rotation, or in different directions. The rotation of each flap 152, 154 takes place relative to a structure 22 of the aircraft
    100 which in the embodiment of the invention presented here is a structure of the wing 104a-b. The crocodile control surface 150 is fixed to the structure 22.
    The two flaps 152 and 154 can thus take a position apart when the air brake function is activated or return to the closed position when the air brake function is deactivated. When the two flaps 152 and 154 are glued to each other, they rotate together in one direction or the other.
    The crocodile control surface 150 also comprises a locking mechanism 220 which alternately takes a locking position in which the upper flap 152 and the lower flap 154 are fixed relative to one another and an unlocking position in which the upper flap 152 and the lower flap 154 are free from each other.
    The establishment of such a locking mechanism 220 thus provides very high rigidity in the locked position and allows freedom of movement of a flap 152, 154 relative to one another in the unlocked position.
    The locking mechanism 220 is controlled by any appropriate control means such as a control unit such as a processor or CPU (“Central Processing Unit” in English) which itself receives orders for example from an aircraft 100 navigation system.
    The unlocking position thus makes it possible to separate the two flaps 152 and 154 when the air brake function is activated or to bring them closer together when the air brake function is deactivated. The locking position allows the two flaps 152 and 154 to be locked, whether they are in the retracted or tightened position.
    The actuation mechanism 210 includes:
    a first actuator 312 fixed to the structure 22,
    a second actuator 314 fixed to the structure 22,
    an upper connecting rod 212 fixed by one end to the upper flap 152 and by another end to the first actuator 312, and
    a lower connecting rod 214 fixed by one end to the lower flap 154 and by another end to the second actuator 314.
    The upper connecting rod 212 and the lower connecting rod 214 are further mounted to be movable in rotation on the structure 22 around the common axis 20. The connecting rods 212 and 214 thus form lever arms which pivot around the common axis 20 when the actuators 312, 314 are actuated. Depending on the direction of the force exerted by the actuator 312, 314 on the connecting rod 212, 214, the corresponding flap 152, 154 will pivot up or down.
    The connection between the connecting rod 212, 214 and the associated actuator 312, 314 is here a pivot connection around an axis of rotation parallel to the common axis 20. The connection between the connecting rod 212, 214 and the flap 152, 154 associated here is a rigid bond.
    In the embodiment of the invention presented in Figs. 2 and 3, and for each connecting rod 212, 214, the common axis 20 is disposed between the two ends of said connecting rod 212, 214.
    The first and second actuators 312 and 314 are preferably jacks which are, for example, electric or hydraulic, and which are controlled by the control unit. In Fig. 3, only the movable rods of the actuators 312 and 314 are seen.
    Fig. 4 shows an enlargement of the locking mechanism 220.
    The upper connecting rod 212 has a first shaft 216 coaxial with the common axis 20 and the lower connecting rod 214 has a second shaft 218 which is hollow and coaxial with the common axis 20 and into which is introduced the first shaft 216 which can rotate therein freely.
    Of course, a reverse arrangement is also possible and one of the connecting rods (here 212) then has a first shaft (here 216) while the other connecting rod (here 214) has a second shaft (here 218) which is hollow and in which is housed said first tree.
    The second shaft 218 and the first shaft 216 are mounted mobile in rotation relative to the structure 22 by means of suitable means such as for example bearings of the structure 22.
    The locking mechanism 220 comprises a jack whose cylinder 402 extends the second hollow shaft 218 and whose piston 404 extends the first shaft 216. Between the bottom of the cylinder 402 and the piston 404 is formed a chamber 410 fluidly connected to a source of energy 412 of the locking mechanism 220.
    In the embodiment of the invention presented in FIG. 4, the jack is hydraulic and the power source 412 is a pump which, on command from the control unit, puts the oil in the chamber 410 under pressure or not.
    In general, the energy source 412 alternately takes a pressurized position in which the energy source 412 puts the fluid contained in the chamber 410 under pressure, which tends to push the piston 404 from the bottom of the chamber 410, and a pressureless position in which the energy source 412 does not put the fluid contained in the chamber 410 under pressure.
    The locking mechanism 220 also has a return means 414 which forces the piston 404 to approach towards the bottom of the chamber 410. The return means 414 here is a helical compression spring which is arranged between the outside of the bottom of the the chamber 410 and a flange 416 integral with the piston 404.
    Part of the inner surface of the cylinder 402 takes the form of a first truncated cone 406 and part of the outer surface of the piston 404 takes the form of a second truncated cone 408. For each truncated cone 406, 408 the small base is oriented towards the chamber 402 and the two truncated cones 406 and 408 have identical angles.
    The two truncated cones 406 and 408 are such that the second truncated cone 408 fits into the first truncated cone 406 and the two truncated cones 406 are arranged so that in the unpressurized position, their lateral surfaces are in contact preventing any movement of one with respect to the other, and so that in the pressurized position, their lateral surfaces are not in contact allowing movements of one with respect to the other.
    Thus, in the pressureless position, the return means 414 constrains the two truncated cones 406 and 408 against each other and block the rotation of the second shaft 218 relative to the first shaft 216, which corresponds to the position of locking of the locking mechanism 220. In the tensioned position, the two truncated cones 406 and 408 move away from each other and allow the rotation of the second shaft 218 relative to the first shaft 216, which corresponds to the unlocking position of the locking mechanism 220.
    To ensure movement of each flap 152, 154 over its entire length, the crocodile control surface 150 includes an articulation mechanism 200 facilitating the rotation of each flap 152, 154 around the common axis of rotation 20 relative to the structure 22 .
    In the embodiment of the invention presented in Figs. 2 and 3, the articulation mechanism 200 comprises for the upper flap 152, a plurality of upper links 202a-b, and for the lower flap 154, a plurality of lower links 204a-b. Still in the embodiment presented here, certain rods 202a, 204a are rigidly fixed to the flap 152, 154 associated and others 202b, 204b are fixed to the flap 152, 154 associated via a pivot link, the axis is parallel to the common axis 20. In addition, each link 202a-b of a flap 152 is fixed to a link 204a-b of the other flap 154 by means of a pivot link whose axis is the common axis 20.
    The rotation of a pair of rods 202a-b and 204a-b around the common axis 20 is ensured for example by a set of bearings made in the structure 22 and in which are fitted shafts 24 on which is also fitted one end of each link 202a-b, 204a-b.
    During the flight of the aircraft 100, it is desirable that the two flaps remain perfectly glued to each other (except in airbrake mode) so that the crocodile control surface 150 behaves as a single element. To do this, whatever the position of the crocodile control surface 150, a force must be applied to each flap 152, 154 in order to guarantee this contact.
    To do this, it is necessary to evaluate the force necessary to ensure this contact. Fig. 5 shows a phase of preparation of the crocodile control surface 150 and FIG. 6 shows an operating phase of the crocodile control surface 150.
    The preparation phase consists in successively replacing each actuator 312, 314 with a shim 502 which prevents the movement of the flap 152, 154 which is associated with the missing actuator 312, 314.
    In Fig. 5, the first actuator 312 is missing and the shim 502 restricts the movement of the upper flap 152, here blocking the movement of the upper rod 212.
    From a neutral position corresponding to an angle Θ, which here is equal to 0 and corresponds to the horizontal, a command is sent to the second actuator 314 so as to force the lower flap 154 against the upper flap 152. It s therefore acts to control a rotation of the lower flap 154 which tends to increase its angle relative to the angle of the neutral position. The command applied tends to move the lower shutter 154 by an angle Θ + <50 inf where <50 inf is counted positively in the direction of the rise of the lower shutter 154. The value <50 inf is such that the positions of the shutters 152 and 154 remain at the angle Θ and that the two flaps 152 and 154 exert between them an interaction force which prevents them from separating in flight.
    The same procedure is carried out for the lower flap 154 by blocking it and applying a force to the upper flap 152 tending to move it by an angle Θ - <50 sup , where <50 sup is counted positively in the direction of ascent. of the upper flap 152. That is to say to decrease the angle of rotation in the trigonometric direction. It is therefore a question of controlling a rotation of the upper flap 152 which tends to decrease its angle relative to the angle of the neutral position.
    According to a particular embodiment <50 inf = <50 sup .
    Fig. 6 shows an example where the crocodile control surface 150 has an angle Θ of -15 ° relative to the horizontal. In flight, when the crocodile control surface 150 is commanded to take a particular position corresponding to an angle Θ, the control unit controls the first actuator 312 to apply to the upper flap 152, an angle 0 - <50 sup to constrain it towards the bottom and the second actuator 314 to apply to the lower flap 154, an angle 0+ <50 inf to constrain it upwards, which guarantees the one-piece behavior of the crocodile control surface 150.
    The adjustment and control of the crocodile control surface 150 have been more particularly described in the case of the actuation mechanism 210 comprising the two actuators 312 and 314 and the connecting rods 212 and 214, but they can be applied more generally within the framework of 210 different actuation mechanisms.
    Thus, in flight, a method for controlling a crocodile control surface 150 comprises:
    a displacement step during which the actuation mechanism 210 moves the two flaps 152 and 154 to an angular position Θ,
    - when the flaps 152 and 154 have reached said angular position Θ, an overload step during which the actuating mechanism 210 applies to each flap 152, 154 a force corresponding to an angular difference <50 inf , <50 sup tendant to reconcile them and previously evaluated during an adjustment step.
    The adjustment step includes:
    a clamping sub-step during which a first flap 152, 154 is clamped to a reference angular position,
    an application sub-step during which a force is applied to the second flap 154, 152, said force tending to press the second flap 154, 152 against the first flap 152, 154,
    - an evaluation sub-step during which the angular difference <50 inf , <50 sup of the second flap 154, 152 and corresponding to the force thus applied is evaluated,
    a clamping sub-step during which the second flap 154, 152 is clamped to the angular reference position,
    an application sub-step during which a force is applied to the first flap 152, 154, said force tending to press the first flap 152, 154 against the second flap 154, 152,
    - An evaluation sub-step during which the angular difference <50 inf , <50 sup of the first flap 152, 154 and corresponding to the force thus applied is evaluated.
    The first part and the second part can be either the upper part 152 or the lower part 154.
    Each <50 inf , <50 sup is evaluated for the first time, during the evaluation sub-steps, by putting force sensors or strain gauges either on the jacks or on each component and by measuring the angle corresponding to the applied force.
    ίο
    权利要求:
    Claims (6)
    [1" id="c-fr-0001]
    1) Crocodile control surface (150) comprising:
    - an upper flap (152),
    - a lower flap (154),
    - an actuation mechanism (210) which ensures the rotational movement of each flap (152, 154) around a common axis (20) either in the same direction or in different directions, and
    - a locking mechanism (220) alternately taking a locking position in which the upper flap (152) and the lower flap (154) are fixed relative to each other and an unlocking position in which the upper flap (152) and the lower flap (154) are free relative to each other.
    [2" id="c-fr-0002]
    2) Crocodile control surface (150) according to claim 1, characterized in that the actuation mechanism (210) comprises:
    - a first actuator (312),
    - a second actuator (314),
    an upper connecting rod (212) fixed by one end to the upper flap (152) and by another end to the first actuator (312), and
    a lower connecting rod (214) fixed by one end to the lower flap (154) and by another end to the second actuator (314), the upper connecting rod (212) and the lower connecting rod (214) being mounted so as to be able to rotate about the 'common axis (20).
    [3" id="c-fr-0003]
    3) crocodile control surface (150) according to claim 2, characterized in that one of the connecting rods (212) has a first shaft (216) while the other connecting rod (214) has a second shaft (218) which is hollow and in which said first shaft (216) is housed, in that the locking mechanism (220) comprises:
    - A cylinder whose cylinder (402) extends the second shaft (218) and whose piston (404) extends the first shaft (216), defining a chamber (410) between the bottom of the cylinder (402) and the piston (404 ),
    - A power source (412) connected to the chamber (410) and adapted to alternately take a pressurized position in which, it puts the chamber (410) under pressure and tends to push the piston (404) from the bottom of the chamber (410), and a pressureless position in which it does not put the chamber (410) under pressure,
    - a return means (414) which forces the piston (404) to approach towards the bottom of the chamber (410), and in that a part of the interior surface of the cylinder (402) takes the form of a first truncated cone (406) and part of the outer surface of the piston (404) takes the form of a second truncated cone (408), the two truncated cones (406) being arranged so that in the unpressurized position , corresponding to the locking position, their lateral surfaces are in contact preventing any movement of one relative to the other, and so that in the pressurized position, corresponding to the unlocking position, their lateral surfaces are not in contact allowing movements of one relative to the other.
    [4" id="c-fr-0004]
    4) Aircraft (100) comprising a structure (22) and at least one crocodile control surface (150) according to one of the preceding claims attached to said structure (22).
    [5" id="c-fr-0005]
    5) Method for controlling a crocodile control surface (150) according to one of the preceding claims, said control method comprising:
    - a displacement step during which the actuation mechanism (210) moves the two flaps (152, 154) to an angular position (Θ),
    - When the flaps (152, 154) have reached said angular position (Θ), an overload step during which the actuation mechanism (210) applies to each flap (152, 154) a force corresponding to an angular difference (ri0 inf , <50 sup ) tending to bring them together and previously evaluated during an adjustment step.
    [6" id="c-fr-0006]
    6) Control method according to claim 5, characterized in that, said adjustment step comprising:
    - a clamping substep during which a first flap (152, 154) is clamped to an angular reference position,
    - an application sub-step during which a force is applied to the second flap (154, 152), said force tending to press the second flap (154, 152) against the first flap (152, 154),
    - an evaluation sub-step during which the angular deviation (<50 inf , <50 sup ) of the second component (154, 152) and corresponding to the force thus applied is evaluated,
    - a clamping sub-step during which the second flap (154, 152) is clamped to the angular reference position,
    - an application sub-step during which a force is applied to the first flap (152, 154), said force tending to press the first flap (152, 154)
    5 against the second part (154, 152),
    - an evaluation sub-step during which the angular deviation (<50 inf , <50 sup ) of the first component (152, 154) and corresponding to the force thus applied is evaluated.
    PL. 1/3
    204a 204b
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    同族专利:
    公开号 | 公开日
    US10518871B2|2019-12-31|
    FR3053956B1|2019-06-28|
    US20180015998A1|2018-01-18|
    引用文献:
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    FR2952348B1|2009-11-10|2012-03-09|Airbus Operations Sas|CROCODILE AERODYNAMIC GOVERNMENT FOR AIRCRAFT|FR3061136B1|2016-12-23|2019-05-24|Safran Electronics & Defense|ELECTROMECHANICAL MOBILE FLYING SURFACE ACTUATOR|
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    法律状态:
    2017-07-24| PLFP| Fee payment|Year of fee payment: 2 |
    2018-01-19| PLSC| Search report ready|Effective date: 20180119 |
    2018-07-25| PLFP| Fee payment|Year of fee payment: 3 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 5 |
    2021-07-27| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1656831A|FR3053956B1|2016-07-18|2016-07-18|CROCODILE GOVERNMENT FOR AIRCRAFT|
    FR1656831|2016-07-18|FR1656831A| FR3053956B1|2016-07-18|2016-07-18|CROCODILE GOVERNMENT FOR AIRCRAFT|
    US15/651,769| US10518871B2|2016-07-18|2017-07-17|Crocodile-type flight control surface for aircraft with locking mechanism for additional stiffness|
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