• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
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    • 专利摘要:
    A system, apparatus and method provide emergency differential braking for controlling an aircraft using the brakes. A braking input device is provided which not only provides emergency and park braking functions, but also allows for differential braking. The braking input device (which may be a lever, a pedal, a park brake and / or emergency brake lever, etc.) may be used in a braking system comprising a brake system control unit ( BSCU), one or more electromechanical actuator control devices (EMAC) and a brake assembly comprising one or more electric actuators. Each EMAC is electrically connected to one or more of the actuators to provide electrical power to drive the actuators. Each EMAC is also connected by communication to the BSCU to receive braking data. In case of emergency, the input device sends the braking signals directly to the brake actuators.
    公开号:FR3038586A1
    申请号:FR1656448
    申请日:2016-07-06
    公开日:2017-01-13
    发明作者:Eric D Cahill
    申请人:Goodrich Corp；
    IPC主号:
    专利说明:

    BACKGROUND OF THE INVENTION The invention relates generally to brakes and more precisely to braking commands providing park braking and emergency functions in an aircraft.
    Aircraft, like other vehicles, have an emergency braking system that activates the brakes for long-term parking and, for a standstill, when the main braking system breaks down. Emergency braking systems of this type may be electrically or hydraulically actuated and are well known to those skilled in the art normally skilled in the art.
    In electrically operated emergency braking systems, a backup braking command signal (in the form of an analog or digital signal) is generated by a lever or emergency brake lever, and this signal is supplied to a brake system control unit (BSCU). The BSCU, on the basis of this signal, orders an electromechanical actuator (EMAC) to activate an actuator. The EMAC, in response to this command from the BSCU, supplies electrical power to an actuator of a braking assembly in order to exert a braking force.
    In addition, electrically actuated braking systems also include a separate emergency brake control box. The emergency brake control unit is configured to control the brake actuators during a failure of the main braking system (eg during a failure of the BSCU). These systems are typically designed to activate all brakes at identical degrees to bring the aircraft to a halt.
    A braking input device is proposed for an emergency braking system which not only makes it possible to implement emergency braking and parking functions, but also allows differential braking in order to carry out the braking control of the brakes. an aircraft. This allows the pilot not only to stop the aircraft in an emergency, but also to pilot the aircraft to the brakes during an emergency stop. More specifically, the braking input device (for example a lever, a pedal, a park brake and / or emergency brake lever, etc.) can be used in a braking system comprising a control system unit. braking system (BSCU), one or more electromechanical actuator control devices (EMAC) and a braking assembly comprising one or more electric actuators. Each EMAC is electrically connected to one or more of the actuators to provide electrical energy to drive the actuators. Each EMAC is also connected by communication to the BSCU to receive braking data.
    Each EMAC may include a switch or the like for selecting a signal to be supplied to the servo compensation network and EMAC drivers. The switch is controlled via a braking mode signal (normal or park / emergency) generated on the basis of the braking input device. The output of the switch is connected to an input of the servo compensation network and to the actuator driver circuits of the EMAC so as to select the signal used by the servocontrol compensation network and the circuits of the actuator. attack intended to control the actuators.
    For normal braking operation, the BSCU generates a braking force signal corresponding to a desired braking force and provides the braking force signal to each EMAC. The processor of each EMAC, based on the brake force signal from the BSCU, generates a brake control signal for the servo compensation network and the actuator driver. During a normal braking mode, the switch selects the signal generated by the EMAC processor and provides this signal to the servo compensation network and the drivers. Thus, global brake control is provided during normal braking through the BSCU and EMAC processors.
    For park braking and / or emergency / brake operation, the braking mode signal supplied to each EMAC is representative of the park / emergency / brake control mode. Based on this mode, the switch directly routes the braking input signal or signals as generated by the braking input device to the servo compensation network and the driver circuits. actuator of the EMAC. The servo compensation network and the driver circuits then control the actuators to exert a braking force. Thus, during a braking / piloting park brake or emergency brakes, the processors BSCU and EMAC are simultaneously avoided and the braking command is directly provided by the braking input device ( for example from the brake lever). This architecture is advantageous because it eliminates the need for a separate (or isolated) backup control box for controlling the EMACs in the event of failure of the main braking system.
    According to one aspect of the invention, a braking input device for supplying emergency braking signals to at least two brake actuators associated with left and right braking assemblies of a vehicle, comprises an actuator member. moving input in a first direction corresponding to a braking level and movable in a second direction corresponding to a relative distribution of the braking level between the first and second braking signals for the control of the at least two brake actuators. The first and second braking signals may be modulated by a pilot during emergency braking to apply differential braking to separate wheels of an aircraft, the apparatus further comprising a park brake locking system for locking the input member at a park brake position and a park brake sensor for detecting when the input device is in park brake mode and generating a response signal to that.
    More specifically, the input member may be linearly movable between first and second positions corresponding to minimum and maximum braking levels, the position of the handle being representative of a desired level of braking. The input member can be rotated around its central axis, the angular position of the input member being representative of a desired distribution of the braking level between the first and second signals. For example, the input member may comprise a lever which is both linearly sliding and rotary. At least one sensor may be provided for detecting a position of the input member and generating the brake signals in response thereto. The input device comprising a park braking position, which can correspond to a maximum braking level.
    According to another aspect, an aircraft braking system comprises at least one braking assembly intended to brake a wheel of an aircraft, the braking assembly including at least one jack intended to exert a braking action in response to a braking signal supplied thereto, and a braking input device as mentioned above, for supplying the braking signal to the actuator.
    According to another aspect, an emergency braking system comprises at least two braking assemblies having actuators for braking respective wheels of an aircraft, and an emergency braking input device for providing braking signals. backup to each actuator. The input device comprises first and second input members for generating first and second braking signals for controlling the at least two braking assemblies, each of the input members being movable between a first position corresponding to a braking level and a second position corresponding to a maximum braking level. The first and second braking signals may be modulated by a pilot during an emergency braking so as to apply a differential braking to separate wheels of an aircraft, the emergency braking system further comprising a braking sensor park for detecting when the input device is in park brake mode and generating a signal in response thereto.
    More specifically, the first and second input members may be pedals. At least one sensor may be provided for detecting a position of an input member and generating a braking signal in response thereto. A park brake interlock system may be provided to lock the input members of the input device to a park brake position, which position may correspond to a maximum braking level. The park brake interlock system may include a latch that holds the first and second input members to the park brake position. In order to achieve the above-mentioned and other objects, the invention therefore includes the features described in more detail below and particularly indicated in the claims. The following description and accompanying drawings show in detail embodiments proposed by way of illustration of the invention. However, these embodiments are only representative of a small number of the various ways in which the principles of the invention can be exploited.
    Fig. 1 is a simple block diagram illustrating an exemplary architecture for controlling an aircraft braking system according to the present invention.
    Figure 2 is a schematic illustration of an example of a multi-actuator computer controlled brake actuation system.
    Figure 3 is a schematic illustration of a brake actuator and associated servo amplifier used in the system of Figure 2.
    FIGS. 4A and 4B are schematic diagrams illustrating an example of a braking input device according to the invention.
    Figs. 5A to 5D are block diagrams illustrating another example of a braking input device according to the invention in various modes of operation.
    Fig. 6 is a block diagram illustrating a side view of the exemplary braking input device of Figs. 5A to 5D.
    Fig. 7 is a block diagram illustrating a top view of the exemplary braking input device of Figs. 5A to 5D, with a sensor system for detecting activation of the device.
    Figs. 8A to 8C are block diagrams illustrating another example of a braking input device according to the invention in various modes of operation.
    Fig. 9 is another diagram of the braking input device of Figs. 8A-8C.
    Figure 10 is a schematic side view of another example of a braking input device.
    FIG. 11 is a schematic top view of the braking input device of FIG.
    Figure 12 is a perspective view of another example of braking input device according to the invention.
    FIG. 13 is a schematic top view of the braking input device of FIG. 12.
    Fig. 14 is a schematic side view of another example of a braking input device.
    Fig. 15 is a schematic plan view of the exemplary braking input device of Fig. 14 in various positions.
    Fig. 16 is a graph illustrating the level of braking command generated by the braking input device of FIGS. 14-15 in various positions.
    The principles of the invention are described below with reference to the drawings. As the invention was designed and developed for use in an aircraft braking system, it will be described hereinafter in this context alone. However, the principles of the invention in their broadest sense can be adapted to braking systems of other types of vehicles. In addition, the following analysis of an example of a multi-actuated computer controlled brake actuation system is provided by way of illustration, with the exception of that which is defined in the appended claims. in this booklet. Therefore, it will be limited to provide details and general functional features of this system so as not to burden the presentation of the invention with details that may vary from one application to another.
    Referring first to FIG. 1, this is an example of an electric braking system 10 having an architecture according to the present invention. The example of an electric braking system comprises a brake system control unit (BSCU) 12 configured to implement braking operations of the aircraft in a conventional manner. The BSCU 12 is configured to receive various inputs from an operator, e.g. left and right pilot brake pedal signals from left and right pilot brake pedals 141 and 14r, and brake pedal signals. left and right co-driver from the left and right co-driver brake pedals 161 and 16r. The brake pedal signals may for example be generated via LVDT devices (variable linear differential transformers - not shown) functionally connected to the respective pedals. When operating the pedals, each LVDT generates a voltage signal corresponding to the degree of operation of the pedal, and this voltage signal can, in the conventional manner, be provided to the BSCU 12. It may be noted that other methods for generating the brake pedal signals may also be used, including encoders, potentiometers, etc.
    The BSCU 12 may also receive other inputs from an operator, for example data from an automatic braking switch 18 for configuring an automatic braking logic. The automatic braking switch 18 may have several settings, such as an enable / disable input, an automatic braking level input (e.g. low, medium, high) and an interrupted take-off input (RTO for Rejected Take- Off) (for example to enable or disable the RTO feature). The BSCU 12 can also receive other aircraft data 20, such as discrete data (for example sensor data, such as the air-ground reference, the retracted position / landing gear output, etc.). , analog data (eg, force data, temperature data, etc.), serial data, etc., as is well known.
    The BSCU 12 is communicatively connected to one or more electromechanical actuator (EMAC) actuators 24, the BSCU 12 providing a braking force signal to the respective EMACs during normal braking operations. It is preferable that the connection is made via a serial communication link, although data can also be exchanged via discrete and / or analog connections. The BSCU 12 is configured to obtain the braking force signal from brake data generated by the pedals 141, 14r, 161, 16r, and / or an automatic brake control and traction control.
    A braking input device 22, which is preferably a combined park / brake braking device (e.g. a joystick, lever, pedal, etc.), provides a braking command signal at each EMAC 24. The braking command signal can be generated by known techniques, for example by means of an LVDT, as previously described with respect to the brake pedals 141, 14r, 161, 16r, or via an encoder or potentiometer configured to provide data corresponding to an actuation or rotation of the braking input device 22. It may be noted that other known methods for generating the braking command signal can also be used. It is preferable for the braking input device to include a mode selector for indicating when normal braking or park / standby is desired. By way of example, the braking input device 22 may comprise contacts which are open when the braking input device is at a first position (for example when it is rotated to the left or pushed inwards), and closed when the braking input device is at a second position (for example when it is rotated to the right or pulled outwards). Alternatively, the braking mode selector may be separate from the braking input device 22. The braking input device 22 may also provide separate braking signals for respective left and right side brakes, such as will be described in more detail below. Further details concerning various braking input devices are provided hereinafter with reference to FIGS. 4A-9.
    The EMACs 24 are electrically connected to one or more actuators 26 of a braking assembly 28, each braking assembly 28 comprising one or more actuators 26, corresponding jacks 30 operatively connected to each actuator 26, and a stack of disks. braking 30 having a plurality of rotors rotatably connected to a wheel 34 and stators rotatably mounted relative to the wheel 34. Each actuator 26 and cylinder 30 are configured to force engage the brake disk stack 30 so as to exert a braking force on a corresponding wheel 34. Wheel speed sensors 36 provide wheel speed data to the BSCU 12 to implement, in the conventional manner, traction control and automatic braking functions.
    As noted above, each EMAC 24 receives the braking force signal from the BSCU 12. In addition to the braking force signal, each EMAC 24 is configured to receive the braking command signal from the input device of the input device. braking 22, and the braking mode signal indicating whether a normal braking operation or a park / rescue braking operation is desired. On the basis of the braking mode signal, each EMAC 24 selects a signal corresponding to the braking force signal provided by the BSCU 12 or the braking command signal provided by the braking input device 22 and, on the base of this signal, control the actuators so that they exert a braking force. Further details regarding the operation of the EMAC are presented below with reference to FIGS. 2 and 3.
    Figure 2 schematically illustrates an exemplary multi-actuated computer-controlled electric brake operating system 10 'to which the principles of the invention can be applied. The main functions of the system 10 'are performed by an EMAC controller 40 and a brake actuator assembly 42. The brake actuator assembly 42 may be mounted in the conventional manner on a wheel assembly. and brake 44 to apply and suppress a braking force exerted on a rotating wheel 34 of this wheel and brake assembly. Wheel speed data is provided to the controller 40 via a wheel speed sensor 36 connected to each wheel 34.
    In the illustrated system example 10 ', the brake actuator assembly 42 comprises at least one, and preferably a plurality of actuators 26, e.g. electro-mechanical actuators (EMAs) 26. The EMAC control device 40 comprises a corresponding number of independent servo amplifiers 46, a microprocessor 48 to which peripherals are associated, and data input / output (I / O) circuits 50. As illustrated, multiples ( for example 4) independent linear electromechanical servocontrol loops operate in a position mode, i.e. the linear position of each actuator is a function of an analog (or equivalent digital) input voltage for a processor. digital signals) applied to a position command input.
    As previously mentioned, the braking input device 22, via a signal generator 22a, generates the braking command signal which is supplied to each EMAC (for example to each amplifier 46 of the EMAC ). Also provided to each amplifier is a braking mode input which is generated via a switch 22b. During normal braking operations, the switch 22b is closed and a braking command is carried out via the BSCU 12 and the EMAC control device 40. However, during park / rescue braking operations the switch 22b is open and each amplifier 46 uses the braking command as supplied by the braking input device 22, thus avoiding the BSCU 12 and the EMAC control device 40. From this In fact, each amplifier may include switching means for selecting either the data generated by the BSCU 12 and the processor 48, or the actual data provided by the braking input device 22.
    FIG. 3 shows in greater detail an example of an electromechanical brake actuator 26 and an associated servo amplifier 46. The brake actuator 26 comprises an electric servomotor 52, a gear train 54 and a reciprocating output cylinder 30. An output cylinder position sensor 56 which provides a position feedback of the actuator, as illustrated, and a force sensor 58 which provides data representative of an applied force by the brake actuator to the brake disk stack are associated with the brake actuator. Although not shown, an engine tachometer providing a speed feedback is also associated with the brake actuator 26.
    The servo amplifier 46 comprises a servo loop compensation network and amplifiers 60 as well as a DC motor drive circuit 62 associated with logic control and current control circuits. More specifically, the servo amplifier 46 may comprise an internal motor current control servo loop 64, an engine speed control servo intermediate loop 66, and a cylinder position servo loop 68. The data Force feedback 69 can be provided to the BSCU to control the force actually applied. Each loop may be compensated for a desired bandwidth behavior, and so as to obtain a uniform dynamic response of all the brake actuators 26. In addition, the servo amplifier 46 includes a means for controlling the motor current and therefore the output force of the brake actuator in response to a force control input. The force control input may be an analog input signal that controls a current level of the motor, while the aforesaid position command input controls the actuator displacement. It can be noted that the analog input signals can be replaced by digital input signals if a digital signal processor is used in the servo amplifier to control the actuators.
    A switch 65 provides an input to the servo loop compensation network 60. It is preferred that the switch 65 be an electronic or software switch. However, a mechanical switch may be used according to the configuration of the EMAC 24. The switch 65 includes a first input 11 configured to receive the braking control signal from the EMAC control device 40 (which in fact comes from the pedals). , 14r, 161, 16R and / or the automatic braking and anti-slip logic from the BSCU 12), and a second input I2 configured to receive the brake command signal from the braking input device 22. An SE selection input of the switch 65 is connected to the mode switch 22a, and an output of the switch 65 is connected to the servo loop compensation network as previously indicated. On the basis of the particular braking mode indicated by the mode switch 22b, the switch 65 provides either the braking control signal (from the EMAC control device 40) or the braking command signal (from the braking input device 22) to the servo loop compensation network 60. Although not shown, scaling logic may be contained in the EMAC to suitably scale the scale. braking command signal so that it can be used by the EMAC circuits. In addition, although the switch is represented as part of the EMAC, it is possible to make the switch separate from the EMAC 24.
    During normal braking, the selection input SE is true and the switch 65 connects the first input 11 to the switch output, thereby connecting the braking control signal from the EMAC controller 40 to the control network. servo loop compensation 60 (and thus to the motor driver 62). Therefore, the movement of each actuator 26 is controlled by the electronic controller 40 (Fig. 2) and the BSCU 12. The microprocessor 48 of the controller 40 provides braking control algorithm processing, temporary data storage. in RAM, a program memory storage, a non-volatile data storage unit, and a control of the servo amplifiers 46 via the input / output circuits 50. The input / output circuits 50 provide digital-to-analog data conversion by generating analog position commands and analog motor current command commands for the four actuators, an analog-to-digital data conversion for monitoring actuator position detection signals and motor current feedback, and discrete signals for auxiliary functions such as motor brake control. Although microprocessors are used in the illustrated preferred embodiment, the processing could be analog and not digital, or could be done in combination with digital processing, as desired.
    In park / rescue braking operations, the BSCU 12 and the controller 40 are both avoided, and the movement of each actuator 26 is directly controlled by the braking input device 22. More precisely, when the braking mode corresponds to park / standby braking, the selection input SE is false, and the switch 65 connects the second input I2 to the output of the switch, thus directly connecting the braking command signal from the device d braking input 22 to the servo loop compensation network 60. Thus, in the event of failure of the main braking system, park / rescue braking can be carried out via each EMAC, without it being necessary. necessary to use a backup control unit. It can be noted that the braking input device 22 can provide braking signals to respective left and right braking assemblies, for example to control the aircraft using the brakes. Further details regarding the braking system are set forth in copending commonly assigned US Patent Application No. A12 / 429303 filed April 24, 2009 entitled "ELECTRIC BRAKE ARCHITECTURE WITH DISSIMILAR EMERGENCY BRAKING PATH", which is hereby incorporated by reference. as a whole.
    Referring now to FIGS. 4A and 4B, these schematically show a braking input device 22 in top view (FIG. 4A) and in side view (FIG. 4B). The exemplary braking input device 22 includes a handle 70 configured to move along a groove or guide 72. At the handle 70 is operatively connected a signal generator 22a such as a potentiometer 22a. , a displacement of the handle 70 along the groove 72 causing a corresponding deflection of a slider arm 23a of the potentiometer. By applying a voltage to the external terminals 23b and 23c of the potentiometer 22a, a braking command signal can be generated on the terminal of the slider arm 23d, which corresponds to the position of the joystick inside the groove (and therefore, at the desired level of braking).
    It should be noted that reference is made to a potentiometer for example only, and that other devices such as an LVDT, an encoder, and so on. can be used instead of the potentiometer to determine the braking command signal. Although not shown in FIG. 4A, the terminals of the potentiometer 22a are electrically connected to the EMAC 24 so as to provide it with the braking command signal.
    Referring further to FIG. 4B, this is a simple schematic side view of the braking input device example 22. The handle 70, in addition to being operably connected to the signal generator 22a, is also functionally connected to the switch 22b. It is preferred that the handle 70 be a push / pull type handle held, which can be held in the extended (pulled) or retracted (pushed) position. When in the "out / pull" position, the switch 22b is in an electrically closed state, and when in the "retracted / pushed" position, the switch 22b is in an electrically open state. The "out / pull" position may correspond to a normal braking mode (ie a brake command being performed via the BSCU 12), while the "retracted / pushed" position may match the park / rescue mode. The switch 22b is electrically connected to the switch 65 so as to provide an indication of the braking mode in progress (normal or park / rescue).
    In another embodiment, the braking input device may include a rotary joystick (rather than a push / pull device). In this embodiment, the rotation of the joystick in one direction (for example to the left) may correspond to a normal braking mode, and the rotation of the joystick in another direction (for example to the right) may correspond to a park / rescue braking operation.
    Therefore, the braking input device 22 can provide both a park / standby brake reference and a mode indicator that can be used to configure the mode of operation of the braking system. This is advantageous because it is sufficient for the pilot to manipulate a single command for the park / rescue braking operation.
    Referring to Figs. 5A-5D and 6, and firstly to Figs. 5A and 6, these show a braking input device 82 which provides functionality similar to that of the braking input device 22 previously described. , but which also facilitates a differential braking for controlling the aircraft using the brakes during an emergency braking. The braking input device 82 is similar to the device 22 both formally and functionally, with the exception of the joystick 70 which is rotatable on its central axis to control a level. braking applied to separate braking assemblies, for example left and right braking assemblies.
    Therefore, the braking input device 82 includes a joystick 70 mounted on a guide 72 for simultaneous sliding and rotational movement, and a pair of side buttons 84 for emergency braking and locking of the joystick 70. in park position, as will be described in more detail below. As for the input device 22 described above, sliding the joystick 70 forward produces an increasing braking signal. However, in this embodiment, rotation of the joystick 70 produces respective left and right braking signals that can be directly applied to each EMAC to provide differential braking. A direction indicator 86 indicates the direction in which the aircraft will be piloted with respect to the forward direction, for example, with respect to the longitudinal axis of the guide 72).
    More specifically, and further referring to the remaining Figures 5B-5D, the input device 82 is shown at various positions corresponding to various braking actions. In Figure 5A, the handle 70 is locked in the rear position, corresponding to an absence of braking activity. The side buttons 84 are not depressed and are used to maintain or otherwise lock the lever to the position shown, to avoid inadvertent operation of the brakes. Figure 6 illustrates a schematic side view of the braking input device 82 at the position of Figure 5A.
    In Fig. 5B, the side buttons 84 have been depressed and the handle 70 has been moved to a position corresponding to a moderate emergency braking. The indicator 86 points directly forward, thus indicating that the braking input device 82 provides first and second identical (or substantially identical) signals to the brake actuators for actuating respective left and right braking assemblies, so that that the aircraft brakes along a line almost straight.
    In FIG. 5C, the handle 70 has been turned counterclockwise so that it now points to the left of the longitudinal axis of the guide 72. This position corresponds to a differential braking (controlled) such as the aircraft tends to turn to the left during an emergency stop. As can be appreciated, the braking input device 82 may be configured to generate respective output signals for the left and right braking assemblies in response to the rotation of the joystick 70. By way of example, when they are rotated to the left, the left brake assembly (s) can be activated more sharply than the right brake assembly (s), effect that the aircraft turns to the left. Conversely, when the joystick is rotated to the right (not shown), the right braking assembly (s) can or can be activated more sharply than the whole or the right braking assembly (s). the left braking assemblies (s), this having the effect that the aircraft turns to the right.
    In FIG. 5D, the lever 70 is in its most forward position, this corresponding to the maximum braking and / or park braking mode. In this case, the side buttons 84 have returned to the outside, indicating that the handle 70 is locked at the parking brake position. Once at this position and the side buttons 84 locked, the braking input device 82 generates a signal representative of the fact that the park brake is applied, as previously described.
    Consequently, the braking input device 82 of FIGS. 5A to 5D facilitates both a differential emergency braking to control the aircraft during an emergency stop, and a park braking function. The exemplary device 82 is intuitive because a braking action is applied by sliding the lever 70 forwards (as if one were operating a pedal), while a differential braking is obtained by rotating the handle 70 in the direction desired by the pilot to pilot the aircraft. The controller 70 could of course be configured to be pulled rather than pushed to generate the brake signal. It may be noted that it is not necessary for the braking input device 82 to have a particular appearance or shape. For example, the handle 70 may be made to resemble the wheels of an aircraft, while the side buttons 84 may be made to resemble wheel chocks. In the illustrated embodiment, the input device is biased toward the position shown in Figure 5A (eg, no braking and no differential braking).
    In addition, the side buttons 84 may be configured to operate in a variety of ways. By way of example, they can restrict any initial movement of the joystick 70 from the position of FIG. 5A until it is actuated. The side buttons can then remain in the actuated state when the joystick is shifted forwards and backwards by the pilot, to return to the locked position only when the joystick 70 returns to the position of FIG. 5A or when engaging the park brake (for example by pushing the lever 70 to the front). The side buttons 84 can then hold the handle 70 to the parking brake position.
    Referring to FIG. 7, this illustrates further details regarding the braking input device 82. The handle 70 is supported so that it can slide and rotate on the guide (not shown in FIG. 7) and is connected to a pair of toothed belts 90a and 90b. Each toothed belt 90a and 90b passes around a respective return pulley 92a and 92b and a respective angular displacement sensor 94a and 94b, thereby connecting the lever 70 to the sensors. The deflection wheels 96 are slidably attached in association with the handle 70 to help guide the timing belts 90a and 90b around the respective sides of the handle 70. The handle 70 and the idlers may also be carried by a carriage 98 which is operatively connected to the guide for a sliding movement.
    It may be noted that the linear (sliding) or rotary displacement of the lever 70 leads to a rotation of the angular sensors 94a and 94b. By way of example, the sliding of the lever 70 towards the left of FIG. 7 leads to a rotation of the two angular sensors 94a and 94b, which rotation can be converted into braking signals and be applied to the actuators, as previously described. . Furthermore, the rotation of the handle 70 in the counterclockwise direction also leads to a rotation of the angular sensors 94a and 94b so that left and right braking signals can be generated. Although the linear position of the handle 70 can only be determined by analyzing the signals produced by the angle sensors 94a and 94b, a linear sensor could also be used to directly measure this displacement. By comparing the signals from each angular sensor 94a and 94b to one another (and / or a linear sensor when present), differential backup braking signals can be generated. It may be noted that redundant sensors could be provided instead of or in addition to the various wheels and / or pulleys.
    Referring now to FIGS. 8A-8C and 9, these illustrate another embodiment of a braking input device generally designated by the numeral 100. In this embodiment, the input device of FIG. braking 100 includes a pair of pedals 104a and 104b. The pedals 104a and 104b may be made to look like aircraft pedals or other pedals. The pedals can be activated by the feet of a pilot, as is the case of conventional pedals, or can be manual commands intended to be activated by the hands of a pilot. In this respect, the pedals can be given an ergonomic shape allowing the hand or the hands of a pilot to grip them, and they can be configured so that they can be pushed or pulled in order to trigger and / or to intensify the braking.
    Each pedal 104a and 104b is functionally connected to sensors 108 (FIG. 9) which detect the displacement of each pedal 104a and 104b (for example an actuation). By way of example, each pedal could be connected to an angular sensor intended to measure a rotation around respective pivot points P of each pedal when a pedal is pressed. Alternatively, a linear displacement sensor could be operatively connected to each pedal to measure the actuation, for example depending on the displacement of the free end of the pedal. The sensors 108 convert the movement of the pedal into respective braking signals which are then applied to the cylinders, as previously described, to implement braking / piloting the emergency brakes. In the position of FIG. 8A, the braking input device 100 is deactivated, and no signal is sent to the actuators (for example, neither the pedal 104a nor the pedal 104b is pressed). In Figure 8B, partially presses the left pedal 104a while the right pedal 104b remains in the position of Figure 8A. This corresponds to a differential braking mode in which the left brakes of the aircraft are activated more pronounced than the right brakes, which causes the aircraft to turn to the left during braking. It is clear that one can press the right pedal weakly or even more strongly than on the left pedal, the latter case leading to a rotation of the aircraft to the right.
    In Fig. 8C, the pedals 104a and 104b are both fully operated, and a park brake latch 110 is positioned above the pedals 104a and 104b to maintain both pedals at the park brake position. It will be appreciated that a switch associated with the park brake latch 110 (Fig. 2) may indicate to the BSCU the moment when the park brake latch 110 is at the position at which the park brake is applied.
    Referring now to Figures 9 and 10, these illustrate another exemplary embodiment. In this embodiment, a joystick 140 having a handle 144 to be grasped by the hand of a pilot is used. The handle 140 is supported so as to be pivotable in a vertical plane at a pivot P1. The lever 140 may for example pivot between a horizontal position and a more vertical position, as illustrated. The movement of the handle 140 between these positions can be detected by a suitable sensor (not shown), such as a rotational motion sensor, and can be used to generate a braking level signal, in a manner similar to that described above with respect to the other embodiments. It can be noted that the larger the angle φ, the higher the overall braking level. A lock / unlock button 148 may be provided to lock the handle at the brake application position (eg at park brake position).
    Referring now to FIG. 11, it will be appreciated that the handle 140 is also configured to pivot in a second plane (e.g., the horizontal plane of FIG. 11). For this purpose, a second pivot point P2 makes it possible to turn the handle 140 to the left and to the right, as illustrated, in order to generate a signal corresponding to the distribution of the overall braking level between the left and right braking assemblies. . The shift to the left of the joystick 140 corresponds to a more pronounced left braking and a less pronounced right braking, leading to steering the aircraft to the left. The displacement of the lever 140 to the right corresponds to a more pronounced right braking and a less pronounced left braking, which leads to steering the aircraft to the right. It may be noted that the larger the angle Θ, the higher the braking force to a given side.
    During operation, a pilot pulls up on the handle 140 by turning the handle 140 by an angle φ to actuate the brakes. To perform differential braking, the pilot can then rotate the joystick to the left or right while holding the joystick at an angle φ.
    In Figure 12, there is illustrated another exemplary embodiment of the braking input device. In this embodiment, the braking input device is a T-handle 200 sliding forward and backward to control the overall braking level, and rotating relative to a central axis A to control differential braking. The T-handle 200 includes a rod 204 which can be connected to appropriate sensors via a carriage, as previously described, or through other means. A joystick portion 208 is supported by the rod 204 so that it can be manipulated by a pilot. A lock button 212 is provided on one side of the joystick portion 204 to lock the handle 200 to a park brake position.
    Referring to Fig. 13, the T-handle 200 is illustrated at various positions corresponding to varying levels of overall braking and / or differential braking. The T-handle 200 is slid forward to go into emergency mode as shown. The T-handle 200 may also be rotated clockwise and counter-clockwise (as illustrated with respect to an axis A in FIG. 12) to control the differential braking. For example, a rotation of the joystick 204 clockwise may correspond to a more pronounced right braking and less pronounced left braking, this tending to turn the aircraft to the right. Conversely, a rotation of the joystick 204 counterclockwise may correspond to a more pronounced left braking and a less pronounced right braking, this having the effect of turning the aircraft to the left. As can be noted, it is possible to actuate the lock button 212 to lock the joystick park position, this corresponding for example to a maximum global braking level in emergency mode.
    Referring to Figures 14 to 16, these further illustrate another example of a braking input device. In this embodiment, the braking input device is in the form of a cantilever lever 220 that can be rotated in a vertical plane around a pivot point P to designate a level braking circuit, and can also be rotated about a differential pivot point PD to designate a differential braking offset, as shown in Figure 15. By way of example, in Figure 14, plus the angle φ is large, the higher the overall braking level. In Fig. 15, the larger the angle Θ, whether positive or negative, the greater the braking bias to a given side. For example, if the handle 220 is rotated clockwise (for example, Θ negative), it is possible to exercise a more pronounced braking on the right brakes and less pronounced on the left brakes whereas if the lever 220 is rotated counterclockwise (for example, Θ positive), it is possible to exert a more pronounced braking on the left brakes and less pronounced on the right brakes.
    To illustrate this concept, Fig. 16 shows the overall braking level and the differential braking offset generated by the handle 220 at various positions. As can be appreciated, the concept illustrated in FIG. 16 can generally be applied to other embodiments described above. The four positions of the joystick 220 on the left side of the graph under the legend "equal left / right braking" correspond to varying degrees of overall braking. The range of positions from about zero degrees PSI to about 45 degrees PSI corresponds to zero overall braking and maximum overall braking, respectively. The intermediate positions illustrate the overall braking degrees between zero and the maximum value. Therefore, the joystick is illustrated at various values of the angle φ, a larger angle corresponding to a larger overall braking level, as described above.
    On the right side of the graph, under the legend "Differential braking", the handle 220 is represented in five different positions H1 to H5, each position corresponding to a different angle Θ. The line L0 represents the angle Θ at these various positions. Positive values of angle Θ correspond to more pronounced left braking and less pronounced right braking, while negative values of angle Θ correspond to more pronounced right braking and less pronounced left braking. On the other hand, the lines Llh and LRH represent the respective left and right braking values for a given angle Θ.
    Beginning with the H1 position, the knob is turned counterclockwise to the left to increase the angle Θ to a positive value. Therefore, Llh denotes an increased left braking level while LRH indicates a reduced right braking level. At the position H2, the lever 220 is turned counterclockwise to the right, leading to a decrease in the value of the angle Θ to zero and, if necessary, to a negative value. As a result, Llh tends to return to zero while LRH increases. At position H3, LRH is positive while l_LH is negative, indicating more pronounced right braking and less pronounced left braking. At the H3 position, the lever 220 is turned counterclockwise to the left, but it remains at a negative angle jusqu'à to the position H4. As a result, LRH grows less rapidly while LH decreases less rapidly. At the H4 position, the handle 220 is rotated counterclockwise to a positive angle Θ so that LRH again goes through zero and then becomes negative, while LH becomes positive.
    Although the invention has been illustrated and described with reference to a certain embodiment or embodiments, various modifications and modifications may of course be apparent to those skilled in the art upon reading this specification and the drawings. attached. With particular reference to the various functions performed by the elements described above (components, assemblies, devices, compositions, etc.), the terms (including when referring to a "means") used to describe these elements are intended to correspond, unless otherwise indicated, to any element that performs the function specified for the element described (ie that is functionally equivalent), even if it is not structurally equivalent to the structure presented which performs the function in the example or examples of embodiment (s) of the invention. Furthermore, while a particular feature of the invention may have been described above with respect to one or more embodiment (s) illustrated, this feature may be combined with one or more other features of the invention. other embodiments, as may be desirable and advantageous for any given or particular application.
    In addition, the invention is considered to cover all conceivable combinations of features described herein, whether or not claimed as such, or whether or not they are presented in one and the same embodiment.
    权利要求:
    Claims (14)
    [1" id="c-fr-0001]
    An emergency braking input device for supplying emergency braking signals to at least two braking assemblies, the device comprising an input member movable in a first direction corresponding to a braking level and movable in a second direction corresponding to a relative distribution of the braking level between first and second braking signals intended to control the at least two braking assemblies, the first and second braking signals thus being able to be modulated during an emergency braking so as to to provide differential braking on separate wheels of an aircraft, the apparatus further comprising a park brake interlock system for locking the input member to a park brake position and a braking sensor of park for detecting when the input device is in park brake mode and generating a signal in response thereto.
    [2" id="c-fr-0002]
    2. The emergency braking input device according to claim 1, wherein the input member is linearly movable between first and second positions corresponding to minimum and maximum braking levels, the linear position of the second gear member. input being representative of a desired braking level.
    [3" id="c-fr-0003]
    3. Emergency braking input device according to claim 1, wherein the input member can be rotated about a central axis, a central position of the input member being representative of a desired distribution of the braking level between the first and second signals.
    [4" id="c-fr-0004]
    The emergency braking input device according to claim 1, wherein the member is a joystick that is linearly movable to indicate a braking level and can be rotated to indicate a relative distribution of the braking level.
    [5" id="c-fr-0005]
    The emergency braking input device according to claim 1, further comprising at least one sensor for detecting a position of the input member and generating braking signals in response thereto.
    [6" id="c-fr-0006]
    The emergency braking input device according to claim 1, wherein the park braking position corresponds to a maximum braking level.
    [7" id="c-fr-0007]
    The emergency braking input device according to claim 1, wherein the input member is pivotable in a first plane to indicate a braking level and is pivotable in a second plane to indicate a relative distribution of the level of braking. braking.
    [8" id="c-fr-0008]
    8. An aircraft braking system comprising at least one braking assembly intended to brake a wheel of an aircraft, the braking assembly comprises at least one actuator for exerting a braking action in response to a braking signal which is provided, and a braking input device according to claim 1 for providing the braking signal to the brake actuator.
    [9" id="c-fr-0009]
    9. An emergency braking system comprising at least two braking assemblies for braking respective wheels of an aircraft, and an emergency braking input device for providing emergency braking signals to each braking assembly, the device input unit having first second input means for generating first and second braking signals for controlling the at least two braking assemblies, each of the input members being movable between a first position corresponding to a minimum braking level and a second position corresponding to a maximum braking level, whereby the first and second braking signals can be modulated during an emergency brake to exert a differential braking on separate wheels of an aircraft, backup brake further comprising a park brake sensor for detecting when the input device is in a braking mode park and generate a signal in response to that.
    [10" id="c-fr-0010]
    The emergency braking system of claim 9, wherein the first and second input members are pedals.
    [11" id="c-fr-0011]
    The emergency braking system of claim 9, comprising at least one sensor for detecting a position of an input member and generating a braking signal in response thereto.
    [12" id="c-fr-0012]
    The emergency braking system of claim 9, further comprising a park brake latch for locking input members of the input device at a park brake position.
    [13" id="c-fr-0013]
    The emergency braking system of claim 12, wherein the park braking position corresponds to a maximum braking level.
    [14" id="c-fr-0014]
    The emergency brake system of claim 12, wherein the park brake latch includes a latch that holds the first and second input members in the park brake position.
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    同族专利:
    公开号 | 公开日
    US10246182B2|2019-04-02|
    US20190176973A1|2019-06-13|
    FR2945029B1|2016-10-14|
    US9216720B2|2015-12-22|
    FR2945029A1|2010-11-05|
    GB2469891A|2010-11-03|
    US20170144750A1|2017-05-25|
    GB2469891B|2014-01-01|
    US9604720B2|2017-03-28|
    US20100276988A1|2010-11-04|
    GB0921978D0|2010-02-03|
    FR3038586B1|2021-09-24|
    US20160059956A1|2016-03-03|
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    法律状态:
    2016-12-02| PLFP| Fee payment|Year of fee payment: 8 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 9 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 11 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 12 |
    2020-12-04| PLSC| Publication of the preliminary search report|Effective date: 20201204 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 13 |
    优先权:
    申请号 | 申请日 | 专利标题
    US12/433,050|US9216720B2|2009-04-30|2009-04-30|Differential emergency/park electric brake system|
    FR0959637A|FR2945029B1|2009-04-30|2009-12-29|ELECTRIC DIFFERENTIAL EMERGENCY / PARK BRAKE SYSTEM|
    FR1656448A|FR3038586B1|2009-04-30|2016-07-06|EMERGENCY DIFFERENTIAL ELECTRIC BRAKING SYSTEM / PARK|FR1656448A| FR3038586B1|2009-04-30|2016-07-06|EMERGENCY DIFFERENTIAL ELECTRIC BRAKING SYSTEM / PARK|
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