• 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 a control member (40) operable by a pilot to control a thrust of an engine system (10) of an aircraft. The controller (40) has a handle (41) and a movable assembly (50) including a handle (55). The handle (55) is connected to the handle (41) by a helical connection (57), a rotation of the handle (55) around the handle (41) generating a translation of the handle (55) and the moving assembly ( 50) along the handle (41), said handle (55) being movable in translation in a first direction (101) of translation, said handle (55) being movable in translation in a second direction (102) of translation opposite to the first translational direction (101).
    公开号:FR3059297A1
    申请号:FR1601695
    申请日:2016-11-30
    公开日:2018-06-01
    发明作者:Jean Romain Bihel；Zouhair SASSI
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    (57) The present invention relates to a control member (40) maneuverable by a pilot to control a thrust of an engine system (10) of an aircraft. The control member (40) includes a handle (41) and a movable assembly (50) comprising a handle (55). The handle (55) is linked to the handle (41) by a helical connection (57), a rotation of the handle (55) around the handle (41) generating a translation of the handle (55) and of the mobile assembly ( 50) along the handle (41), said handle (55) being movable in translation in a first direction (101) of translation, said handle (55) being movable in translation in a second direction (102) of translation opposite to the first direction (101) of translation.
    Control device, rotary wing aircraft and method
    The present invention relates to a control member, a rotary wing aircraft comprising such a control member, and a method applied by the aircraft.
    A rotary wing aircraft of the helicopter type for example comprises at least one main rotor which at least partially participates in the lift and propulsion of this aircraft.
    In addition, there is at least one system to control the yaw movement of the aircraft.
    Consequently, such a helicopter comprises three piloting axes. A first axis consists in using a first command to control the standard of the lift vector of the aircraft. A second axis consists in using a second command to control the orientation of this lift vector, and a third axis consists in using a third command to control the yaw movement of the aircraft.
    For example, a helicopter may include a main rotor participating in its propulsion and its lift. In addition, a helicopter may include an auxiliary rotor participating at least in controlling the yaw movement.
    Consequently, the aircraft comprises piloting commands maneuverable by a pilot to control the developments of this aircraft.
    Thus, a collective pitch lever collectively controls the pitch of the main rotor blades to adjust the lift of the aircraft. A cyclic stick makes it possible to cyclically control the pitch of the blades of the main rotor in order to adjust the orientation of the lift vector of the aircraft. Finally, a lifting beam collectively adjusts the pitch of the blades of the auxiliary rotor to control the helicopter's yaw movement.
    According to another embodiment, a helicopter can comprise two main rotors, possibly coaxial.
    Therefore, a collective pitch lever can collectively control the pitch of the main rotor blades to adjust the lift of the aircraft. A cyclic stick can be used to cyclically control the pitch of the main rotor blades to adjust the orientation of the lift vector of the aircraft. Finally, a lifting beam can be used to adjust the yaw torque exerted by at least one main rotor on the fuselage of the aircraft, in order to control the yaw movement of the aircraft.
    Another type of rotary wing aircraft known as "hybrid" for convenience comprises at least one rotor which participates at least partially in the lift and propulsion of this aircraft. In addition, the aircraft includes a device for controlling the yaw movement of the aircraft. This aircraft also comprises an engine system capable of exerting, at least according to the direction of advance of the aircraft, a thrust known as "additional thrust" for convenience. This additional thrust is qualified as "additional" insofar as this thrust is axially independent of the thrust possibly exerted by the rotary wing.
    In addition to the three usual piloting axes, such a hydride rotary wing aircraft comprises a fourth piloting axis. This fourth steering axis consists in using a fourth command to control the standard of the additional thrust.
    For example, a hybrid rotary wing aircraft can comprise a main rotor which at least partially participates in the lift and propulsion of this aircraft. In addition, this hybrid rotary wing aircraft comprises two engine systems provided respectively with two propellers participating at least partially in the propulsion of the aircraft and in the control of the yaw movement of this aircraft.
    A collective pitch lever can be used to collectively control the pitch of the main rotor blades to adjust the standard of the lift vector of the aircraft. A cyclic stick can be used to cyclically control the pitch of the main rotor blades to adjust the orientation of the lift vector of the aircraft.
    In addition, a thrust control can allow a pilot to collectively adjust an average pitch of the propeller blades to control the additional thrust jointly generated by the propellers.
    In addition, a spreader can be used to adjust the distribution of this additional thrust between the two propellers to control the yaw movement of the aircraft through the application of different thrusts using the propellers. This lifting beam can for example make it possible to adjust a differential pitch, the pitch of the blades of a propeller being for example equal to the sum of the average pitch and half of the differential pitch, the pitch of the blades of the other propeller being for example equal to the difference of the average step and half of the differential step.
    The thrust control can take the form of an "all or nothing" electric control command. When the thrust control is operated, this thrust control generates an order to increase or reduce the average pitch of the propeller blades. This order is transmitted to actuators to modify the pitch of the blades of the two propellers in the same way. For example, an actuator is arranged on a mechanical transmission chain controlling a hydraulic distributor, this hydraulic distributor supplying a hydraulic cylinder capable of causing movement of the blades of a propeller.
    The documents FR 1518834 and GB 790560 are cited by way of illustration only because these documents do not relate to the control of propellers of a hybrid helicopter.
    Document FR 1518834 presents a lever control. This lever is movable. The movement is guided by a guide having a λ-shaped guide slot (lambda). In addition, the lever carries a rotary handle controlling the fuel intake of an engine unit.
    GB 790560 presents an aircraft order. This control comprises a tube movable in rotation about a transverse axis of rotation. The tube is connected to a control rod for the collective pitch of the blades of a rotor. A rotation of the tube then induces a modification of this collective pitch.
    In addition, this control is provided with a rod passing through the tube. This rod extends longitudinally from a handle projecting towards the front of the tube towards an end projecting towards the rear of the tube. This end is articulated to a mobility system controlling the position of a valve. The handle can rotate relative to the tube about a longitudinal axis between a first position and a second position.
    When the handle is in the first position, a rotation of the tube around its transverse axis of rotation only induces a modification of the collective pitch of the rotor blades.
    On the other hand, when the handle is in the second position, a rotation of the tube around its transverse axis of rotation induces a modification of the collective pitch of the rotor blades and of the position of the valve controlled by the handle.
    Consequently, the documents FR 1518834 and GB 790560 present controls provided with rotary handles only.
    The object of the present invention is therefore to propose an innovative control member which can be operated by a pilot and which can in particular be used to control a thrust of an aircraft.
    The invention thus relates to a control member maneuverable by a pilot, this control member being intended to control an engine system exerting a thrust in an aircraft, the control member comprising a handle and a movable assembly arranged on the handle and movable relative to this handle, the mobile assembly comprising a handle.
    Such an engine system can for example take the form of a reactor or even a propeller.
    The handle is linked to the handle by a helical connection so that a rotation of the handle around the handle generates a translation of the handle and of the mobile assembly along the handle, the handle being mobile in translation according to a first direction of translation for example intended to impose an increase in thrust, the handle being movable in translation in a second direction of translation opposite to the first direction of translation and for example intended to impose a reduction in said thrust.
    For convenience, the thrust is subsequently considered to be positive when this thrust makes it possible to advance the aircraft, according to a direction of advance going from the tail towards the nose of the aircraft, and negative otherwise.
    The term "increase" refers to an increase in thrust. Such an increase can in particular make it possible to reverse the direction of the thrust by transforming a negative thrust into a positive thrust. An increase in thrust can amount to imposing an acceleration of the aircraft depending on the direction of travel.
    The term "decrease" refers to a decrease in thrust. Such a reduction can in particular make it possible to reverse the direction of the thrust by transforming a positive thrust into a negative thrust. A reduction in thrust can amount to imposing a deceleration of the aircraft depending on the direction of travel.
    Consequently, the mobile assembly of the control member has a handle in helical connection on the handle. Such a handle can take the form of a cylinder which locally surrounds a tube of the handle.
    Therefore, the control member does not have a handle movable only in rotation, unlike document FR 1518834 for example, or only movable in translation. The handle performs a rotation-translation movement through the helical connection. As the handle is turned around the handle, this handle is moved in translation.
    Thus, a pilot can intuitively move the handle to increase or reduce the thrust exerted by each engine system controlled by the control member.
    In addition, a pilot grabbing the grip of a hand can exert a significant effort on a mechanical transmission connected to the mobile assembly. Indeed, the total force exerted by the pilot on the mechanical transmission results from a combination of an effort developed in rotation by his hand to turn the handle and of a force developed in translation exerted by the arm of the pilot. Such a combination of effort cannot be achieved with a conventional handle, and can prove advantageous for moving elements requiring significant control efforts.
    In addition, a handle with a helical connection can be positioned precisely by a pilot relative to the handle, unlike a handle movable only in translation.
    Finally, the control means embodied by the mobile assembly of the control member is purely mechanical. Its operation is materialized by the rotary actuation of a handle, which generates a translational action of the mobile assembly comprising this same handle. This mobile assembly is mounted on the handle, for example a handle controlling the collective pitch of a main rotor, and its operation may not influence the command generated by the handle as such.
    By its structure and for the reasons mentioned above, this control member can tend to be robust, ergonomic, practical, and to be used intuitively.
    This control member can thus be used on a hybrid helicopter to control the thrust exerted collectively by the propellers. In this case, the handle can for example allow emergency management of the thrust exerted by the propellers. The rotation of the handle generates, thanks to a helical mounting, a longitudinal displacement of the handle on the handle in order to help the pilot to grasp the direction of the variation of thrust (acceleration forward, deceleration backward) . Optionally, the rotational movement of the handle can also be indexed to the movement of a needle of a dash needle indicator.
    The control unit may also include one or more of the following characteristics.
    Thus, the control member may include a mechanical movement transmission, said mechanical movement transmission comprising at least one movable link mechanically fixed to the mobile assembly.
    The expression “mechanical movement transmission” designates a mechanical system provided with at least one link which can be moved at least partially in a linear fashion. Such a transmission can for example comprise at least one ball control having a blade movable in translation, a cable control having a cable movable in translation, a connecting rod, etc.
    The mechanical movement transmission then extends from an input portion comprising a link linked to the mobile assembly to an output portion. For example, a single link extends from the inlet portion to the outlet portion. The translation of the mobile assembly following the rotation of the handle generates an identical translation of the inlet portion and then a movement of the outlet portion. For example, the outlet portion performs a translation of the same amplitude and / or the same direction as the inlet portion and the mobile assembly.
    A movement order is thus generated purely mechanically.
    According to another aspect, the mobile assembly may include a base which cooperates with the handle, the handle being articulated to the base by a pivot link giving a degree of freedom in rotation to the handle relative to the base and around the handle, the base being mounted on the handle by a sliding link, the handle being movable in rotation relative to the base and being integral in translation with the base, the base being only movable in translation relative to the handle.
    Optionally, the mechanical movement transmission is fixed to the base.
    The use of a handle and a base attached to a mechanical movement transmission makes it possible to move the input portion of the mechanical transmission linked to the base only in translation.
    According to another aspect, the mobile assembly can be intended to control a control actuator requiring a displacement of this mobile assembly over a control amplitude to cover a whole operating range of this pilot actuator. Out of operation, the mobile assembly is in a centered position between a first stop and a second stop, the first stop and the second stop being reached by the mobile assembly from the centered position following a translational movement of the assembly. movable according to said control amplitude.
    The handle may be an emergency control system. Thus, the handle can be made inoperative in certain operating phases, for example outside a case of failure of a main control interface driving the control actuator or outside of drive phases.
    This device then makes it possible to ensure that the mobile assembly can control the control actuator over the entire operating range of this control actuator, regardless of the state of the control actuator when the handle is made operative. .
    For example, the handle is free to rotate over a maximum amplitude of plus or minus 270 degrees which generates a translation of the mobile assembly of plus or minus 75 millimeters with regard to the centered position and a predetermined direction of positive movement. In other words, and from the centered position, a rotation of the handle by 270 degrees in a first direction of rotation induces a translation of 75 millimeters in the first direction of translation. Likewise, and from the centered position, a rotation of the handle by 270 degrees in a second direction of rotation induces a translation of 75 millimeters in the second direction of translation.
    The maximum displacement capacity of the mobile assembly is then 150 millimeters, double the total useful travel provided for the control actuator.
    As an illustration, the thrust effort developed by the pilot is around 10 daN (decanewton) at the handle outlet.
    According to another aspect, the handle can extend longitudinally from a proximal end to a free end, the proximal end being provided with a hinge giving the handle a degree of freedom in rotation about an axis of rotation.
    The first direction of translation can go from the proximal end to the free end.
    In particular, the first direction is parallel if necessary with the direction of advance towards the front of the aircraft.
    The operation of the control is then intuitive because the movement of the mobile assembly towards the front of the handle implies a variation in the longitudinal thrust towards the front (acceleration) of the aircraft. Conversely, actuation of the handle towards the rear implies a variation in the longitudinal thrust towards the rear (deceleration).
    According to another aspect, the handle can be arranged between said proximal end and said free end, the handle being independent of the handle so that a rotation of the handle around its axis of rotation does not induce a displacement of the handle along of the handle.
    In addition to a control member, the invention also relates to an aircraft. This aircraft is provided with at least one engine system exerting a thrust, the thrust being regulated by at least one control actuator, the control actuator being controlled by a chain of transmission of a movement leading to the control actuator . The aircraft then comprises at least one control member according to the invention, this control member being mechanically connected to the chain of transmission of a movement and being intended to move the chain of transmission of a movement.
    In addition, the movement transmission chain can comprise at least one pilot actuator, this pilot actuator being piloted by an avionics control interface solicited by a pilot.
    The term “command interface” designates a member activated by a pilot, such as for example a button or the like, a touch screen, a voice command, etc.
    The term "avionics" means that the control interface generates an electrical, electrical, digital, or optical signal to control a change of state of the actuator, namely the relative movement of two parts of this actuator. For example, the control member requires the extension or retraction of the actuator in the context of a linear actuator, a rotation of a rod in the context of a rotary actuator, or a deformation in the context of 'a piezoelectric actuator.
    This command interface can be a main system used by default.
    Conversely, the control member does not require a change of state of the pilot actuator, but moves this pilot actuator mechanically. The control unit can be a backup means used in the event of a failure of the control interface or during training phases.
    According to another aspect, the aircraft possibly comprising two propeller engine systems, the thrust exerted by each propeller of an engine system being controlled by modifying a pitch of the blades of this propeller, the aircraft may include a control system maneuverable by a pilot to modify the thrusts exerted by the two propellers in a different way, the control member making it possible to modify the thrusts exerted by the two propellers in the same way, the chain of transmission of a movement comprising at least one combiner connected to the control member and the control system as well as the two propellers, the combiner mechanically combining a displacement generated by the control member and a displacement generated by the control system.
    The combiner can be of a known type. For example, the teaching of document FR 3027871 is applicable.
    According to another aspect, the control member possibly comprising a mechanical movement transmission integral in translation with the mobile assembly, a lever can be articulated on the one hand to the mechanical movement transmission and on the other hand to the chain of transmission of a movement, said lever being movable in rotation about an axis of articulation.
    A simple lever serves as an interface between the two subsystems, which turns out to be simple to implement.
    The aircraft may comprise several control members, each comprising a mechanical movement transmission connected to the mobile assembly of the associated control member, each mechanical movement transmission being articulated with the lever.
    For example, a pilot command and a co-pilot command are of the type of the controller according to the invention. The mobile assemblies of the two control members are then connected to the same lever. The combination of orders between these two control members is thus naturally achieved by this common lever.
    According to another aspect, the articulation axis possibly extending between two end zones of the lever, the mechanical movement transmission and the movement transmission chain can be articulated to the lever between the articulation axis and the same extreme zone.
    The lever may not generate a change in direction of a movement.
    According to another aspect, the aircraft may include an immobilization system maneuverable by a pilot to immobilize the lever in normal operation, namely for example as long as the control actuator can be piloted without maneuvering the handle of the ordered.
    In normal and therefore nominal operation, the lever is locked in one position. If necessary, the lever serves as an anchor point for an electrically controlled pilot actuator. On the other hand, the lever is unlocked if necessary to allow the control of the control actuator by the mobile assembly of a control member according to the invention.
    The immobilization system can be provided with a mechanical system which comprises a movable blocking finger in translation and an opening in the lever, the locking finger being engaged in said opening to prevent rotation of the lever in normal operation and being disengaged from this orifice to allow rotation of the lever in manual operation.
    The finger may be integral in translation with a gripping means so that it can be operated by a pilot.
    The invention also relates to a method for controlling an engine system of an aircraft according to this invention.
    According to this method, the handle is rotated in a first direction of rotation to translate it along the handle in the first direction of translation in order to increase the thrust exerted by the motor system, and the handle is rotated in a second direction of rotation to translate it along the handle in the second direction of translation to reduce the thrust exerted by the motor system.
    Optionally, the aircraft may have an indicator having a scale illustrating thrust values and a needle pointing on this scale a value of a current thrust, said needle rotating in a first direction of movement when the thrust increases and according to a second direction of movement when the thrust decreases, said first direction of rotation is identical to said first direction of movement, said second direction of rotation is identical to said second direction of movement.
    Maneuvering the handle can be intuitive in many ways.
    Indeed, the handle can move longitudinally in a homogeneous manner to the order of thrust given as indicated above.
    In a complementary or alternative manner, the handle can move in rotation in a homogeneous manner with the movement of the needle illustrating this thrust on an indicator.
    For example, a rotation of the handle in a dextrorsum direction can induce a displacement of the needle in this same dextrorsum direction.
    The invention and its advantages will appear in more detail in the context of the description which follows with examples given by way of illustration with reference to the appended figures which represent:
    - Figures 1 and 2, diagrams illustrating a control member according to the invention, and
    - Figure 3, a diagram illustrating a control member having a homogeneous operation to the operation of a thrust indicator,
    FIG. 4, a view of an aircraft according to the invention,
    - Figures 5 and 6, diagrams illustrating an architecture for controlling engine systems of said aircraft.
    The elements present in several separate figures are assigned a single reference.
    FIG. 1 shows a control member 40 according to the invention in three dimensions, and FIG. 2 kinematically represents the control member 40. This control member 40 is intended to control a motor system 10 exerting a thrust, for example in an aircraft 1.
    Referring to Figure 1, the control member 40 has a handle 41. This handle 41 extends from one end called "proximal end 42" to one end called "free end 43". The proximal end 42 can be articulated to a floor by an articulation 70. This articulation 70 can confer on the handle 41 a degree of freedom in rotation only around an axis of rotation AX2. Thus, the handle 41 can represent a collective pitch lever, the rotation of the handle controlling by known methods a modification of a collective pitch of the blades of a rotor. A collective step lever is hereinafter referred to as a "collective step lever" so as not to be confused with an interface lever according to the invention.
    In addition, the free end 43 can carry various control buttons. In particular, this free end 43 can carry an avionics control interface 18 controlling said thrust under normal conditions.
    Furthermore, the control member has an additional mechanical control arranged on the handle. This command takes the form of a movable assembly 50 which is arranged on the handle 41 and movable in translation along this handle 41.
    The movable assembly 50 includes a handle 55. Such a handle 55 can take the form of a cylinder surrounding the handle.
    This handle 55 is linked to the handle 41 by a helical connection 57.
    Such a helical connection 57 may comprise at least two guide members including a helical rail 58 having a predetermined screw pitch and a pin 59 sliding in the helical rail 58. One of said two guide members is then secured to the handle 41 and the other guide member is integral with the handle 55. For example, a helical rail 58 is hollowed out in a surface of the handle 41 and a pin 59 projects from an internal surface of the handle 55 so as to be arranged in the rail in propeller 58. Alternatively, a helical rail 58 is hollowed out in an internal surface of the handle, and a pin 59 projects from the surface of the handle so as to be arranged in the helical rail of the handle.
    Consequently, a rotation of the handle 55 around an axis of extension of the handle 41 generates a translation of the handle 55 and of the mobile assembly 50 along this axis of extension. Such an extension axis can represent an axis of symmetry of the section of the handle along which the mobile assembly moves.
    In addition, the handle 55 is independent of the handle 41. A rotation of the handle around its axis of rotation AX2 therefore does not induce a movement of the handle 55 and of the mobile assembly 50 relative to the handle 41.
    Furthermore, the control unit 40 presented comprises a mechanical movement transmission 36. This mechanical movement transmission 36 is mechanically fixed to the mobile assembly 50 to transfer an order given by the mobile assembly through a movement.
    To facilitate the arrangement of the mechanical movement transmission, the mobile assembly 50 may include a base 60 which cooperates with the handle 55. The handle 55 is then connected to the base 60 by a pivot link 62 which gives a degree of freedom in rotation with the handle 55 relative to the base 60.
    For example, the base takes the form of a housing 61 in which is placed one end of the handle. This end can only rotate around the extension axis with respect to the housing 61, apart from the operating clearances.
    In addition, the base 60 is fixed to the handle 41 by a slide connection 65. The slide connection 65 may comprise two guide means including a long rail 66 and a pin 67 sliding in the long rail 66, one of the two guide means being integral with the handle 41 and the other guide member being integral with the base 60. For example, an elongated rail 66 is hollowed out in the handle 41 and a pin 67 is fixed to the base 60 to slide in the elongated rail 66. The rail elongate 66 can be arranged following the helical rail 58 if necessary.
    Consequently, the handle 55 is movable in rotation relative to the base 60. On the other hand, the handle 55 and the base 60 are integral in translation along the handle 41.
    As a result, a link of the mechanical movement transmission 36 is advantageously fixed to the base 60, so as not to undergo the rotary movement of the handle 55 and to move only in translation.
    Therefore, a rotation of the handle 55 in a first direction of rotation 103 can induce a displacement in translation of the movable assembly 50 in a first direction of translation 101, for example to require an increase in the thrust exerted by the motor systems orders. Conversely, a rotation of the handle 55 in a second direction of rotation 104 opposite to the first direction of rotation 103 can induce a displacement in translation of the movable assembly 50 in a second direction of translation 102 opposite to the first direction of translation , for example.
    require a decrease in said thrust.
    The first direction of translation 101 can be directed substantially along the direction of advance AV of an aircraft and from the proximal end 42 towards the free end 43. The expression “substantially according to the direction of advance AV” means that the direction of translation is parallel to a vertical plane passing through the direction of advance, and perpendicular to the pitch axis of the aircraft for example.
    Furthermore and with reference to FIG. 3, the first direction of rotation and the second direction of rotation can be homogeneous to the operation of an indicator 80.
    Indeed, the aircraft may include an indicator 80 which has a scale 81 illustrating thrust values. In addition, the indicator 80 has a needle 83 movable in rotation which points on this scale a value of a current thrust, namely the thrust developed by the motor systems. This needle 83 rotates in a first direction of movement 105 when the thrust increases, and in a second direction of movement 106 when the thrust decreases. The second direction of movement 106 is opposite to the first direction of movement 105.
    Therefore and according to the method applied, a pilot can turn the handle 55 in the first direction of rotation 103 to translate it along the handle 41 in the first direction of translation 101 in order to increase the thrust exerted by the engine systems 10 controlled, and rotates the handle 55 in the second direction of rotation 104 to translate it along the handle in the second direction of translation 102 to reduce the thrust exerted by the motor systems 10 controlled.
    More precisely, the first direction of rotation 103 can be identical to the first direction of movement 105, and the second direction of rotation 104 is identical to the second direction of movement 106.
    The operation of the mobile assembly is therefore highly intuitive.
    Furthermore, the mobile assembly can be moved between two extreme positions, and for example between a first stop 201 and a second stop 202.
    When the mobile assembly is made inoperative, for example, said mobile assembly 50 can be in a position called "POSO centered position" not visible in FIG. 1. In this centered position, the mobile assembly 50 is equidistant from the first stop 201 and second stop 202.
    If this mobile assembly 50 is intended to control at least one control actuator 14 requiring a displacement of the mobile assembly 50 over a predetermined control amplitude to cover the entire operating range of this control actuator 14, said distance is equal to said control amplitude. From the POSO centered position, the first stop 201 or the second stop 202 are reached by the mobile assembly 50 following a translational movement of the mobile assembly according to said control amplitude.
    FIG. 4 shows an aircraft 1 according to the invention. This aircraft 1 is provided with at least one control member 40 for controlling at least one engine system 10. This engine system exerts a thrust making it possible to move the aircraft 1.
    This aircraft 1 comprises a fuselage 2 which extends longitudinally in a forward direction of advance of the aircraft from a tail 3 to a nose 4.
    Aircraft 1 can be a rotorcraft. Consequently, the aircraft can comprise at least one rotor 3 which at least partially participates in the lift of the aircraft or even in its propulsion. Such a rotor 3 can be carried by the fuselage 2. This rotor comprises a plurality of blades with variable pitch.
    Furthermore, this aircraft also comprises at least one engine system capable of exerting, at least according to the direction of advance of the aircraft, a thrust. For example, the aircraft 1 comprises two engine systems 10 respectively provided with two propellers 11, 12. The two propellers 11, 12 can be arranged transversely on either side of the fuselage and carried by one wing 7.
    Each propeller 11, 12 comprises a plurality of blades 13 with variable pitch.
    The propellers 11, 12 and the rotor 3 can be set in motion by a conventional power plant 15. Such a power plant can include at least one engine as well as various power transmission boxes, for example.
    To be controllable by a pilot, the aircraft comprises a cyclic control 5 maneuverable by a pilot to cyclically control the pitch of the rotor blades 3 in a customary manner. The cyclic control 5 can take the form of a usual cyclic handle for example.
    In addition, the aircraft comprises a collective control 7 maneuverable by a pilot to collectively control the pitch of the rotor blades 3 in the usual manner. The collective control can take the form of a collective pitch lever for example.
    The collective control and the control unit 40 can form one and the same equipment.
    In addition, an avionics control interface 18 can allow a pilot to collectively adjust the thrust exerted by the propellers, for example by adjusting a mean pitch of the propeller blades. Consequently, a control system 16, possibly a spreader bar, can for example make it possible to adjust a differential pitch, the pitch of the blades of a propeller being for example equal to the sum of the average pitch and half of the differential pitch, the not of the blades of the other propeller being for example equal to the difference of the average pitch and half of the differential pitch.
    In this context, the control unit 40 according to the invention can then represent an emergency system making it possible to control the average pitch in the event of failures of the avionics control interface 18 or during flight training, for example. The collective control 7 can then include the handle 41 of the control member 40. The avionics control interface can be carried by this handle 41.
    However, the control member 40 according to the invention can also be arranged on other types of aircraft, for example to control the thrust of a reactor.
    FIG. 5 schematically illustrates a piloting architecture on an aircraft of the type of FIG. 4.
    According to this architecture, the pitch of the blades 13 of each propeller can be modified. Thus, the aircraft comprises for each propeller an actuator called for convenience "control actuator 14" which modifies the pitch of the associated blades on command.
    The control actuators 14 are controlled by a conventional control chain called “motion transmission chain 20” for convenience. This movement transmission chain can be controlled by the control system 16 and the control interface 18.
    This control interface 18 can be an avionics command generating a signal transmitted to at least one actuator 17 of the chain for transmitting a movement. Such an actuator is referred to as a "pilot actuator" for convenience.
    Consequently, the pilot actuators and the spreader are mechanically connected to a combiner 22, this combiner 22 being connected to each control actuator 14. This combiner 22 can take the form of a conventional combiner.
    Furthermore, this architecture has a mechanical back-up system which can be used in particular in the event of a failure of the control interface 18.
    This backup system includes at least one control member 40 according to the invention. FIG. 5 illustrates the possible presence of a control member 40 operable by a pilot and of a control member 40 operable by a co-pilot.
    Each control member 40 comprises a movable assembly 50 which is movable in translation and mechanically connected by a mechanical movement transmission 36 to a single lever 31. This lever 31 is thus articulated on the one hand to each mechanical movement transmission 36 and d on the other hand to the chain of transmission of a movement 20.
    In addition, the lever cooperates with an immobilization system 37 which makes the lever 31 inoperative on request.
    When the lever is inoperative under normal operating conditions, the lever serves as an anchoring point for the pilot actuators 17. A change of state of the pilot actuators 17 in fact induces a movement of the combiner. The control unit then does not control the control actuators. The mobile assemblies of each control member are stationary in their repositories.
    On the other hand, when the immobilization system 37 releases the lever 31, a translation of a mobile assembly 50 induces a movement of the combiner 22.
    FIG. 6 presents the various organs of the architecture of FIG. 2.
    According to FIG. 6, each movable assembly 50 of the control members 40 is connected to a common lever 31 by a mechanical movement transmission 36. Such a mechanical transmission can comprise a sheath 361 bearing against a support 362. In addition, the transmission mechanical movement 36 may include a cable or a blade passing through the sheath to be fixed to the mobile assembly 50 and to the lever 31.
    Furthermore, the lever 31 is articulated to a stationary member of the aircraft by an articulation which gives the lever 31 a degree of freedom in rotation about an axis of articulation AX1. The lever extending along the length between two end zones 32, 33, the hinge axis AX1 is positioned between these end zones 32, 33.
    Consequently, each mechanical movement transmission 36 is optionally articulated to the lever 31 between the articulation axis AX1 and a particular extremal zone.
    Furthermore, an immobilization system 37, if necessary, makes it possible to immobilize the lever 31 on request. This immobilization system 37 can comprise a rod, one end of which represents a locking finger 38. This locking finger 38 can be inserted into a hole 39 in lever 31 to prevent rotation of lever 31 about its axis of articulation AX1. The rod can also include a gripping means 380. Consequently, a pilot can take hold of the gripping means 380 to remove the locking finger from the orifice 39 in order to release the lever 31.
    According to another aspect, the movement transmission chain 20 is articulated to the lever 31 between this axis of articulation AX1 and this same particular extremal zone. When the lever 31 is immobilized by the locking finger 38, this lever thus serves as an anchor point for the movement transmission chain.
    In accordance with the embodiment shown in FIG. 6, this movement transmission chain 20 comprises at least one pilot actuator 17 controlled by a control interface 18 or even by an automatic pilot system. In addition, this movement transmission chain 20 can comprise connecting rods, deflection means, a combiner 22 ... This combinator 22 can be connected by ball controls, or even by connecting rods to the control actuators 14. The movement transmission chain 20 is shown schematically.
    Consequently, when the immobilization system immobilizes the lever 31, the pilot actuators 17 are piloted to change state and transmit an order in displacement by a mechanical control connected to each control actuator 14. The lever 31 then isolates the chain of transmission of a movement of the control members 40.
    When a pilot releases the lever 31 by requesting the immobilization system 37, a displacement of a mobile assembly 50 induces a displacement of at least one link of a mechanical movement transmission 36, a rotation of the lever 31, then movement of members of the movement transmission chain 20, and finally of an input of the control actuators 14.
    Naturally, the present invention is subject to numerous variations as to its implementation. Although several embodiments have been described, it is understood that it is not conceivable to identify exhaustively all the possible modes. It is of course conceivable to replace a means described by an equivalent means without departing from the scope of the present invention.
    权利要求:
    Claims (16)
    [1" id="c-fr-0001]
    1. Control member (40) maneuverable by a pilot, said control member (40) being intended to control an engine system (10) exerting a thrust in an aircraft (1), said control member (40) comprising a handle (41) and a mobile assembly (50), the mobile assembly (50) being arranged on the handle (41) and movable relative to this handle (41), said mobile assembly (50) comprising a handle (55), characterized in that said handle (55) is linked to the handle (41) by a helical connection (57) so that a rotation of the handle (55) around the handle (41) generates a translation of the handle (55) and of the movable assembly (50) along the handle (41), said handle (55) being movable in translation in a first direction (101) of translation, said handle (55) being movable in translation in a second direction (102 ) of translation opposite to the first direction (101) of translation.
    [2" id="c-fr-0002]
    2. Control member according to claim 1, characterized in that said control member (40) comprises a mechanical movement transmission (36), said mechanical movement transmission comprising at least one mobile link mechanically fixed to the mobile assembly ( 50).
    [3" id="c-fr-0003]
    3. Control member according to claim 2, characterized in that said movable assembly (50) comprises a base (60) which cooperates with said handle (55), said handle (55) being articulated to the base (60) by a connection pivot (62) giving a degree of freedom in rotation to the handle (55) relative to the base (60) and around the handle, said base (60) being mounted on the handle (41) by a slide link (65), said base (60) being only movable in translation relative to the handle (41), the handle (55) being movable in rotation relative to the base (60) and being integral in translation with the base (60), said mechanical movement transmission (36) being fixed to said base (60).
    [4" id="c-fr-0004]
    4. Control member according to any one of claims 1 to 3, characterized in that said mobile assembly (50) controlling a control actuator (14) requiring movement of the mobile assembly (50) over a control amplitude to cover an entire operating range of this control actuator (14), when not in operation, said movable assembly (50) is in a centered position (POSO) between a first stop (201) and a second stop (202), the first stop (201) and the second stop (202) being reached by said mobile assembly (50) from the centered position (POSO) following a translational movement of the mobile assembly according to said control amplitude.
    [5" id="c-fr-0005]
    5. Control member according to any one of claims 1 to 4, characterized in that said handle (41) extending longitudinally from a proximal end (42) to a free end (43), said proximal end (42 ) being provided with a joint (70) giving the handle a degree of freedom in rotation about an axis of rotation (AX2), said first direction of translation (101) goes from the proximal end (42) to the free end (43).
    [6" id="c-fr-0006]
    6. Control member according to any one of claims 1 to 5, characterized in that said handle (41) extending longitudinally from a proximal end (42) to a free end (43), said proximal end (42 ) being provided with a joint giving the handle a degree of freedom in rotation about an axis of rotation (AX2), said handle (55) is arranged between said proximal end (42) and said free end (43), said handle (55) being independent of the handle (41) so that a rotation of the handle (41) about its axis of rotation (AX2) does not induce a displacement of the handle (55) along the handle (41).
    [7" id="c-fr-0007]
    7. Aircraft (1) provided with at least one engine system (10) exerting a thrust, said thrust being regulated by at least one control actuator (14), said control actuator (14) being controlled by a transmission chain a movement (20) leading to said control actuator (14), characterized in that said aircraft (1) comprises at least one control member (40) according to any one of claims 1 to 6, said member control (40) being mechanically connected to the movement transmission chain (20) and being intended to move said movement transmission chain (20).
    [8" id="c-fr-0008]
    8. Aircraft according to claim 7, characterized in that said movement transmission chain (20) comprises at least one pilot actuator (17), said pilot actuator (17) being piloted by a control interface (18 ) avionics maneuverable by a pilot.
    [9" id="c-fr-0009]
    9. Aircraft according to any one of claims 7 to 8, characterized in that said aircraft (1) comprising two engine systems (10) with propellers (11, 12), the thrust exerted by each propeller (11, 12) d 'an engine system being controlled by modifying a pitch of blades (13) of this propeller, said aircraft (1) comprises a control system (16) maneuverable by a pilot to modify the thrusts exerted by the two propellers in a different manner, said control member (40) making it possible to modify the thrusts exerted by the two propellers in the same way, said movement transmission chain (20) comprises at least one combiner (22) connected to the control member (40) and to the control system (16) as well as to the two propellers (11, 12), said combiner (22) mechanically combining a movement generated by said control member (40) and a movement generated by said control system (16) .
    [10" id="c-fr-0010]
    10. Aircraft according to any one of claims 7 to 9, characterized in that said control member (40) comprising a mechanical movement transmission (36) fixed to the mobile assembly (50), a lever (31) is articulated on the one hand to the mechanical movement transmission (36) and on the other hand to the said movement transmission chain (20), said lever (31) being movable in rotation about an axis of articulation (AX1).
    [11" id="c-fr-0011]
    11. Aircraft according to claim 10, characterized in that said aircraft (1) comprising several control members (40) which each comprise a mechanical movement transmission (36) connected to the mobile assembly (50) of the associated control, each mechanical movement transmission (36) is articulated to the lever (31).
    [12" id="c-fr-0012]
    12. Aircraft according to any one of claims 10 to characterized in that said articulation axis (AX1) extending between two end zones (32, 33) of the lever (31), the mechanical movement transmission (36) and the movement transmission chain (20) are articulated to the lever (31) between said articulation axis (AX1) and the same end zone (33).
    [13" id="c-fr-0013]
    13. Aircraft according to any one of claims 10 to
    12, characterized in that said aircraft (1) comprises an immobilization system (37) maneuverable by a pilot to immobilize said lever (31) in normal operation.
    [14" id="c-fr-0014]
    14. Aircraft according to claim 13 characterized in that said immobilization system (37) is provided with a mechanical system which comprises a locking finger (38) movable in translation and an orifice (39) of the lever (31), said locking finger (38) being engaged in said orifice (39) to prevent rotation of the lever (31) in normal operation and being disengaged from said orifice (39) to allow rotation of the lever (31) in manual operation.
    [15" id="c-fr-0015]
    15. Method for controlling an engine system (10) of an aircraft (1) according to any one of claims 7 to 14, characterized in that the handle is turned (55) according to a first direction of rotation (103) to translate it along the handle (41) in the first direction of translation (101) in order to increase the thrust exerted by the motor system (10), and the handle (55) is turned in a second direction of rotation ( 104) to translate it along the handle in the second direction of translation (102) in order to reduce the thrust exerted by the motor system (10).
    [16" id="c-fr-0016]
    16. Method according to claim 15, characterized in that said aircraft (1) having an indicator (80) having a scale (81) illustrating thrust values and a needle (83) pointing on this scale a value of one
    5 current thrust, said needle (83) performing a rotation in a first direction of movement (105) when the thrust increases and in a second direction of movement (106) when the thrust decreases, said first direction of rotation (103) is identical to said first direction of movement (105), said
    10 second direction of rotation (104) is identical to said second direction of movement (106).
    1/3
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    同族专利:
    公开号 | 公开日
    FR3059297B1|2018-11-09|
    CN108116674B|2020-12-29|
    EP3330177A1|2018-06-06|
    EP3330177B1|2019-04-24|
    CN108116674A|2018-06-05|
    KR20180062430A|2018-06-08|
    US10737775B2|2020-08-11|
    US20180148167A1|2018-05-31|
    KR101977153B1|2019-05-10|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2514212A|1948-08-25|1950-07-04|Firestone Tire & Rubber Co|Control lever for aircraft and the like|
    GB790560A|1955-06-02|1958-02-12|Saunders Roe Ltd|Improvements in helicopters|
    FR1518834A|1967-02-10|1968-03-29|Sud Aviation|Control arrangement of a combined lift and jet propulsion helicopter and gyroplane and related controls|
    US2788676A|1953-03-19|1957-04-16|Harley Davidson Motor Co Inc|Twist grip bowden wire operator|
    FR1318834A|1961-02-01|1963-02-22|Gen Electric Co Ltd|Improvements to electrical systems intended to provide a digital representation of the position of a moving part|
    US3936015A|1974-06-28|1976-02-03|United Technologies Corporation|Retractable collective pitch stick|
    US4241687A|1978-11-13|1980-12-30|Outboard Marine Corporation|Throttle control for a marine propulsion device|
    US5340342A|1993-06-02|1994-08-23|Brunswick Corporation|Universal tiller handle with shift and throttle|
    US5370017A|1993-07-07|1994-12-06|Krauer; Alwin|Handlebar cable control with biased return feature|
    US7770490B1|2006-03-31|2010-08-10|Streamline Designs Inc.|Motor throttle assembly|
    US7775136B2|2007-08-13|2010-08-17|Schwulst Kyle E E|Twist-grip handlebar controller|
    CN101723091B|2009-12-16|2012-04-18|李游|Rotor wing pitch change control device of heligyro|
    US9067672B2|2012-02-10|2015-06-30|Bell Helicopter Textron Inc.|Pilot control system with pendent grip|
    FR2991663B1|2012-06-07|2014-06-13|Sagem Defense Securite|MINIMANCHE OF PILOTAGE OF AN AIRCRAFT|
    PL2979978T3|2014-07-31|2017-02-28|Airbus Helicopters Deutschland GmbH|A control system for controlling collective and cyclic pitch of rotor blades of a multi-blade rotor in a rotary-wing aircraft|
    FR3027871B1|2014-10-30|2018-03-23|Airbus Helicopters|MECHANICAL DEVICE FOR COMBINING AT LEAST ONE FIRST ORDER AND A SECOND ORDER ORDER, AND AN AIRCRAFT PROVIDED WITH SUCH A DEVICE|
    CN204489183U|2014-12-17|2015-07-22|中国航空动力机械研究所|Pitch joystick structure|US10689096B2|2018-02-26|2020-06-23|Bell Helicopter Textron Inc.|Adjustable cyclic stick|
    CN109018431B|2018-08-13|2020-02-18|燕山大学|Double-helix locker of automatic tilter of main rotor testing machine|
    CN109625247A|2018-11-30|2019-04-16|中国航空工业集团公司沈阳飞机设计研究所|A kind of adjustable aircraft side lever arm support|
    FR3093077B1|2019-02-27|2021-01-22|Airbus Helicopters|assisted deflection device and aircraft|
    法律状态:
    2017-11-21| PLFP| Fee payment|Year of fee payment: 2 |
    2018-06-01| PLSC| Search report ready|Effective date: 20180601 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 4 |
    2021-08-06| ST| Notification of lapse|Effective date: 20210705 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1601695A|FR3059297B1|2016-11-30|2016-11-30|CONTROL UNIT, AIRCRAFT WITH ROTATING VESSEL AND METHOD|
    FR1601695|2016-11-30|FR1601695A| FR3059297B1|2016-11-30|2016-11-30|CONTROL UNIT, AIRCRAFT WITH ROTATING VESSEL AND METHOD|
    EP17200291.7A| EP3330177B1|2016-11-30|2017-11-07|A control member, a rotary wing aircraft, and a method|
    CN201711235178.4A| CN108116674B|2016-11-30|2017-11-30|Control member, rotorcraft and method|
    US15/826,851| US10737775B2|2016-11-30|2017-11-30|Control member, a rotary wing aircraft, and a method|
    KR1020170163381A| KR101977153B1|2016-11-30|2017-11-30|A control member, a rotary wing aircraft, and a method|
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