KR101983203B1 - An electric control member, a rotary wing aircraft, and a method - Google Patents

Abstract

The present invention relates to an electric control device (1) having an operation means (3). The electric control device (1) has a first measuring system (10) and a second measuring system (20), wherein the first measuring system (10) and the second measuring system (20) respectively perform first measurement and second measurement at a current position of the operation means (3). A processor unit (30) compares the first measurement and the second measurement for generating a control signal (ORD) as a function of the current position, and when the first measurement and the second measurement do not correspond to the same position with respect to the operation means, the operation means (3) is regarded in a neutral position.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to an electric control member, an electric control member, a rotor wing,

Cross-reference to related application

This application claims the benefit of FR 16 01481, filed October 12, 2016, which is incorporated herein by reference in its entirety.

The present invention relates to an electric control member, a rotary wing including such a control member, and a method applied by the rotary wing.

A helicopter type rotor blade has at least one main rotor that contributes to providing at least some of its lift and propulsion to the rotor blade.

In addition, there is at least a system that serves to control yaw movement of the wing.

In such a situation, such a helicopter has three steering axes. The first axis uses a first control to control the magnitude of the lift vector of the rotating wing. The second axis uses a second control to control the orientation of the lift vector and the third axis uses a third control to control the yaw movement of the rotating wing.

For example, a helicopter may have a main rotor that contributes its thrust and its lift. In addition, the helicopter may have an auxiliary rotor which at least contributes to controlling yaw movement.

In such a situation, a collective pitch lever makes it possible to collectively control the pitch of the blades of the main rotor to adjust the lift of the rotating wing. A cyclic stick serves to periodically control the pitch of the blades of the main rotor to adjust the orientation of the lift vector of the rotor. Finally, the pedal acts to collectively adjust the pitch of the blades of the auxiliary rotor to control the yawing motion of the helicopter.

In another embodiment, a helicopter may possibly have two main rotors on a common axis.

In such a situation, the collective pitch lever may serve to collectively control the pitch of the blades of the main rotor to adjust the lift of the rotating wing. The cyclic stick may serve to periodically control the pitch of the blades of the main rotors to adjust the orientation of the lift vector of the rotational wing. Finally, the pedal can serve to adjust the torque exerted by the at least one main rotor on the body of the rotary wing to control the yaw movement of the rotary wing by applying different torques.

Another type of flywheel known as " hybrid " for convenience has at least one rotor that at least partially contributes to providing lift and propulsion to the flywheel. Such a rotor blade also has a device for controlling its yaw movement. Such a rotor blade unit also has a system suitable for exerting a thrust, which is referred to as " additional " thrust, at least in the direction of travel of the rotor. This additional thrust is called "additional" as long as it is axially independent of the thrust exerted by the rotor blade.

In addition to the three common steering axes, such hybrid wingers have a fourth steering axis. This fourth axis uses the fourth control to control the magnitude of the additional thrust.

For example, a hybrid rotor blade may have a main rotor that contributes at least partially to providing lift and propulsion thereto. In addition, the hybrid rotor blade has a propulsion system that at least partially propels the rotor blade and has two propellers at least partially contributing to controlling yaw motion of the rotor.

The collective pitch lever can serve to collectively control the pitch of the blades of the main rotor to adjust the magnitude of the lift vector of the rotational wing. The cyclic stick serves to periodically control the pitch of the blades of the main rotor to adjust the orientation of the lift vector of the rotational wing.

In addition, the thrust control may enable the pilot to adjust the mean pitch of the blades of the propeller collectively to control the additional thrust generated jointly by the propeller.

In addition, the pedals can play a role in adjusting the manner in which this additional thrust is shared between the two propellers to control the yawing movement of the rotating wing by applying different thrusts to each of the propellers. For example, such a propeller can serve to adjust the differential pitch, the pitch of the blades of one propeller is equal to the sum of the average pitch plus the differential pitch, and the pitch of the blades of the other propeller is equal to For example, the difference between the average pitch and the half of the differential pitch.

The thrust can have the form of on / off control. When the thrust control is steered, the thrust control generates an instruction to increase or decrease the average pitch of the blades of the propellers. This command is sent to the actuators to modify the pitch of the blades of both propellers in the same way. For example, the actuator is disposed on a mechanical connection device that controls the hydraulic valve, and such hydraulic valve is for supplying to the hydraulic actuator suitable for generating the movement of the blades of the propeller.

Such thrust control is advantageous. However, in order to make it possible to request a sharp increase in power produced by the power plant that drives the propeller, it is too slow to modify the average pitch of the blades, or in fact, when flying near other aircraft, It can be too fast to have precise control over the advancing speed of the aircraft.

In addition, the flight control independent of the thrust control can position the blades of the propellers at a predetermined position, in particular during the phase of the autorotation flight.

In order to enable the propellers to be controlled in the event of a thrust control malfunction, an emergency mechanical control may also be provided. This mechanical control may include a mechanical lever suitable for mechanically moving the mechanical connection device for controlling the hydraulic valve.

와 Agusta Westland AW609

로 알려져 있는 항공기에는 틸팅(tilting) 로터가 구비되어 있다. 명령들은 회전익기의 세로 추력이 로터들을 운반하는 나셀(nacelle)들이 기울어지게 함으로써 제어되는 것을 가능하게 하고, 그로 인해 "헬리콥터" 작동 모드와 "비행기(airplane)" 작동 모드 사이의 전이(transition)를 제공한다. 그렇지만, 그러한 상황은 하이브리드 회전익기의 프로펠러들을 제어할 때 마주치는 문제들과는 관계가 적다.The trademark Bell V-22

And Agusta Westland AW609

There is a tilting rotor on the aircraft. Commands enable the longitudinal thrust of the rotating wing to be controlled by tilting the nacelles carrying the rotors, thereby causing a transition between the " helicopter " operating mode and the " airplane & to provide. However, such a situation has little to do with the problems encountered when controlling the propellers of a hybrid rotary wing.

Patent WO2016 / 043943A2 reverts to the concept of on / off control for varying the pitch of propelling propellers or propellers, adding the possibility of requesting zero thrust from the propelling propeller (s).

Document FR2984004 describes a rotary control device with a control wheel and a return device that tends to return the wheel to the neutral position. The indexing device serves to hold the wheel in at least one position relative to the support. Such a control device also has a printed circuit with a sensor for detecting the movement of the wheel.

Document FR2984004 has little to do with the present invention because it is not related to controlling additional thrust in a hybrid rotary wing.

Documents WO2015 / 181525 and document US2011 / 140690 are also known.

Document WO2015 / 181525 describes an electric control device having manipulation means and a support. Such a control device includes a sensor for measuring the current position of the operating means, and also has a force sensor.

Document US2011 / 140690 describes an electric control device having an operating means and a support. Such a control device includes a sensor for measuring the current angular position of the operating means.

It is therefore an object of the present invention to propose a new control device which can be used in particular to control the thrust of a rotary wing.

The invention therefore relates to an electrical control device having an operating means and a support, such operating means being movable relative to the support, the operating means being intended to be moved relative to the support by a person, And a first measurement system for making a first measurement of the current position of the operating means with respect to the first measurement system.

Such an electrical control apparatus includes a second measurement system for performing a second measurement of the current position, such first measurement system and second measurement system being independent and unrelated, and for generating a control signal as a function of the current position Wherein the processor unit is deemed to be in the neutral position when the first measurement and the second measurement do not correspond to the same position with respect to the operating means.

In such a situation, the processor unit may generate an audible and / or visible alarm that a fault has been detected.

The term " manipulation means " is used to refer to a member operable by a person. In particular, this term refers to a movable member of an electrical switch. For example, such an operating means may include a wheel capable of rotational movement with respect to a support, a lever, and the like.

The terms " first measurement " and " second measurement " refer to data that varies as a function of the position of the operating means relative to the reference. For example, the angular position of the wheel drive relative to the reference is measured through the first measurement and the second measurement. In such a situation, with respect to two different positions of the operating means, each of the first and second measurements must have two different values.

The term " independent and dissimilar " means that the first measurement system and the second measurement system generate different kinds of signals, even if all of the signals are about the position of the manipulation means. The first measurement and the second measurement represent different data, even if they all indicate the position of the manipulation means. For example, the first measurement depicts the position of the manipulation means in the form of a current having a constant voltage, and the second measurement depicts the position of the manipulation means in the form of a binary value.

Therefore, the present invention does not use a single measurement system for measuring the position of the operating means.

Conversely, the electrical control unit has two dissimilar measuring systems, each of which measures the position of the operating means.

The first measurement and the second measurement may pass through two different paths to reach the processor unit. The first measurement and the second measurement are compared to verify that the measurement system is operating correctly.

For example, each measurement may be associated with a respective order to be given. If the first measurement and the second measurement relate to two different orders, then the processor unit deduces the existence of an inconsistency.

Alternatively, each value of the first measurement may be associated with a theoretical value that must be reached by the second measurement. The processor unit then determines if the second measurement corresponds to the stored theoretical value. If not, the processor unit deduces the existence of a mismatch.

If there is a mismatch, the processor unit deduces that the measurement system has failed. In such a situation, the processor unit generates a stored predetermined control signal corresponding to the neutral position of the operating means. In this case, the processor unit ignores the information transmitted by the first measurement system and the second measurement system.

In the event of a mismatch, an invalid state may also be generated to determine whether a signal corresponding to the neutral position has been sent as a result of the mismatch or as a result of an operating means entering such a neutral position.

Alternatively, the processor unit may generate a control signal corresponding to the most recent coincident measurement.

If there is a mismatch, an invalid state may also be generated.

If there is no inconsistency, the processor unit generates a predetermined and stored control signal corresponding to the first measurement and the second measurement.

This feature makes it possible to obtain a device that tries to avoid common modes of failure so as to achieve an optimized level of reliability and safety. Therefore, the electric control device is suitable for controlling the main function of the rotary wing, such as the longitudinal thrust of the hybrid rotary wing.

For example, the first measurement and the second measurement may be performed using the COM (COM) and MONITOR (MON) architectures that require the measurements prepared by the two independent channels to be matched with respect to the action to be taken Can be considered to control the actuators acting on the thrust, in which case the actuator (s) will not cause any action if the received measurements are not similar.

The availability of independent and dissimilar measurements makes it possible to prevent one malfunction from occurring during measurement without causing unwanted commands by downstream software processing via two independent calculation channels.

The electrical control device may also include one or more of the following features.

Thus, the first measurement system may comprise means for delivering a first measurement in the form of a first signal of an analog type, and the second measurement system may comprise means for delivering the second measurement in the form of a second signal of a digital type .

Therefore, the first measurement system can send an analog signal. In such a situation, the first measurement may take the form of a current that provides a voltage that varies as a function of the position of the operating means over a range of, for example, 0 V to 12 V.

Conversely, the second measurement system carries a digital signal. This second measurement may therefore be, for example, a digital measurement of the " reflected binary " type. Specifically, the second measurement system can apply gray codes.

For example, the first measurement system may include an active electrical sensor or a Hall effect sensor or potentiometer for sensing the rotational movement, in which case the first measurement may provide a voltage dependent on the current position Is expressed in the form of a first signal.

One active electrical sensor of rotational motion is known as the weak word RVDT, which corresponds to the term rotary variable differential transformer.

The second measurement system may also include a code wheel forced to rotate with the operating means and the processor system cooperating with the code wheel to determine a current binary value corresponding to the current position, Is expressed in the form of a second signal including the binary value.

The processor system may be a conventional optical or magnetic system.

The code wheel generates pure binary code. The code wheel makes it possible to transmit a digital signal dependent on the motion made by it.

For example, such a code wheel is in the form of a perforated wheel. The processor system generates a light beam that illuminates the measurement surface of the wheel. Depending on the position of the wheel, the light beam passes through the wheel through a perforation, in which case it reaches the sensor or else it is blocked and blocked on the measuring surface of the wheel. When the sensor detects the presence of the beam, the sensor produces an electrical signal.

For example, to obtain a 3-bit digital signal, it is possible to use three beams and three sensors. For example, a binary signal having some other number of bits, such as a binary signal having four bits, may be considered.

The degree of rotation of the code wheel is encrypted using a gray code. Gray codes, also known as "alternate binary", are used to change only one bit at a time when the number is increased by one (unity), thereby avoiding possible transient transients.

In another aspect, the electrical control device may include a return system that tends to return the operating means to a neutral position.

Such a return system may include a tiny gas actuator or spring associated with the mechanical pedestal that prevents the mechanical abutment from acting beyond its return to the neutral position.

The return system tends to mechanically return the operating means to a neutral position and hold them there. Therefore, when a person moves the return means, the person exerts a force against the force exerted by the return system. When the person releases the operating means from the hand, the return system moves the operating means to the neutral position.

In such a situation, malfunction of the return system does not result in unwanted rotation of the operating means, which can be most advantageous when the electrical control device controls the sensitive system of the rotating wing.

For example, the return system may include a first spring and a second spring, each of which is provided with a first movable end and a second movable end, the operating means including a first movable end and a second movable end, Wherein the return system includes a pedestal, the first spring abuts the pedestal in a first direction to position the actuating member in a neutral position, the first spring The second spring tends to move the second movable end about the circumference by abutting the pedestal in the second direction to position the operating member in the neutral position .

In another aspect, the electrical control device may comprise a holding system which tends to retain the operating means in at least one " indexed " with respect to the support.

Such retention systems may take the form of, for example, a notch system having a bearing ball and a resilient member. This holding system can therefore be of the type described in document FR2984004.

Alternatively or additionally, such a retention system may be a friction system. Such a friction system includes a member that abuts and rubs against the operating means in order to have a tendency to retain the operating means in any position.

Such a retention system can define a plurality of switch positions where the operating means can be found with respect to the support, and each position theoretically generates different measurements for both the first and second measurements.

The return system tends to have operating means at each location. When the return system is present, it delivers a return force greater than the holding force exerted by the retention system to the manipulation means. Therefore, the retention system plays a role in ensuring that the operating means is held in place when the return system is broken. Therefore, the malfunction of the mechanical return system in the neutral position does not cause undesired rotation of the operating means even in the presence of vibrations, and in particular in the rotating wing cockpit, as the retention system works.

In another aspect, an electrical control device may provide a first assembly provided with a support together with an operating means, a first measurement system, and a second measurement system, wherein the processor unit is attached to the first assembly, Wherein the processor unit is for connecting to at least one computer that is physically independent of the first assembly and wherein the processor unit sends the control signal to such a computer so that both the first measurement and the second measurement When the first measurement and the second measurement do not correspond to the same position of the operating means, the control signal is related to the control signal in the parameter of the value established as a function of the measured position of the operating means when the measured position corresponds to the position, Is related to the neutral position.

The control signal may also include validity information. In such a situation, the control signal may indicate an order resulting from an order mismatch associated with the neutral position or a spontaneously given command.

In this first variant, the operating means, the first measuring system, the second measuring system, and the processor unit comparing the measurements are controlled by at least one computer of the autopilot system via at least one bus, It is incorporated into a single piece of equipment suitable for transmitting instructions. In this case, the electric control device can be easily integrated into, for example, a rotor blade.

The generic CAN corresponds to the term "controller area network", which specifies a bus of a particular tie.

For example, the processor unit may take the form of a programmable logic circuit. A programmable logic circuit is a logic integrated circuit that can be reprogrammed after it has been fabricated. Such an array has a plurality of discrete logic cells and a logic bistable that can be freely interconnected. A programmable logic circuit may take the form of an electronic component known as a " field-programmable gate array " (FPGA).

For example, the processor unit generates a control signal to control the propulsion system of the rotating wing and sends it to the computer of the autopilot system.

In a second variant, the electric control device provides a first assembly provided with a support together with operating means, a first measuring system and a second measuring system, the processor unit not being attached to the first assembly, Wherein the processor unit is optionally connected to the first assembly by at least one bus and the bus is connected to a first measurement system and a second measurement system, Wherein the control signal relates to a parameter of a value established as a function of the measured position of the operating means when both the first measurement and the second measurement correspond to the measured position, When the measurement does not correspond to the same position of the operating means, it relates to the neutral position.

In this second variant, the operating means, the first measuring system and the second measuring system are all integrated in the same piece of equipment. Such equipment is connected to the remote processor unit via, for example, a CAN bus or a wired connection.

For example, the processor unit may be an integral part of an autopilot system that controls the propulsion system of the aircraft

In addition to the electrical control device, the present invention provides an aircraft having at least one main rotor that at least partially contributes to providing lift to an aircraft, such aircraft comprising at least one propulsion system that is separate from the main rotor, The propulsion system generates a thrust called the " additional " thrust for at least partially contributing to the advancement of the aircraft.

The aircraft also includes an electrical control device of the present invention which is connected to the propulsion system to control the additional thrust and which at least in part controls the rate of change of the additional thrust transmitted to the propulsion system Demand.

For example, the operating means is mounted on a collective pitch lever that collectively controls the pitch of the blades of the main rotor.

In addition, the propulsion system may include at least one propeller, with a pitch correction system for modifying the pitch of the blades of the propeller.

In such a situation, and depending on the change, the processor unit may be connected to an autopilot system relating to the propulsion system, or it may be part of such an autopilot system and is connected to a pitch correction system acting on the pitch of the blades of the propellers.

Independently of the variant, operating the operating means does not cause the on / off control to occur only to increase or decrease the additional thrust. Specifically, operating such operating means causes control signals to be generated to control the rate of change of the additional thrust.

The rate of change can be, for example, the rate of change of the additional thrust directly expressed in watts per second, or it can be the rate of change of the pitch of the blades of the propeller, which is expressed in degrees of pitch per second, .

Therefore, the electric control device enables the speed at which the additional thrust is changed to be precisely controlled.

The aircraft may also include one or more of the following features.

Therefore, and in one variant, the propulsion system comprises at least one propeller having a plurality of variable pitch blades, wherein such propulsion system comprises a pitch correction system for modifying the pitch, the processor unit being connected to the pitch correction system .

In another aspect, an aircraft may include an emergency electrical handling member coupled to the propulsion system to require a zero rate of variation with respect to additional thrust or to position the average pitch of the blades of the propeller at a predetermined position. Positioning the blade of the propeller at the evacuation site optimizes the workload the pilot receives.

The emergency electric operating member may have priority over the electric control apparatus, and it must be independent of the operating means, and in this case, the operating means is suppressed when the emergency electric operating member is operated.

In order to avoid the non-timely application of the emergency electrical operating member, it is possible to use a mechanical device for protecting the operating means. Avionics control may also be used for suppression from such functions.

According to a variant, the emergency electrical operating member may be connected to a computer that is in communication with the processor unit, or actually to the processor unit.

The emergency electrical operating member may be used during the flight phase of automatic rotation, or when the operating means is subject to jamming.

The use of the emergency electrical operating member makes it possible to invalidate the control received from the operating means and to force a return to the evacuation thrust control position.

In another aspect, an aircraft may include an emergency machine operating member coupled to the propulsion system.

For example, the emergency machine operating member may have the form of a lever acting on a power transmission drive connected to the servo-control to control additional thrust, for example by controlling the pitch of the blades of the propeller.

The present invention also provides a method of controlling an aircraft propulsion system.

This method includes the following steps:

- generating a first measurement and a second measurement;

Comparing the first measurement and the second measurement; And

Generating a rate of change with respect to the pitch or additional thrust of the blades of the propulsion system in order to control an additional thrust as a function of the position of the operating means relative to a reference, Position of the operating means when the second measurement corresponds to the measured position of the operating means at the same time and when the first and second measurements do not correspond to the same position of the operating means, Is set to zero.

If there is a discrepancy between the first measurement and the second measurement, a visible or audible alarm may be generated by the alarm system.

The method may also include one or more of the following steps.

For example, the step of comparing the first measurement with the second measurement may include the following stages:

Determining a first rate of variability corresponding to the first measurement by using the relationship giving the first rate of variance as a function of the first measurement;

Determining a second rate of variance corresponding to the second measurement by using the relationship giving the second rate of variance as a function of the second measurement; And

And - comparing the first rate of variance with the second rate of variance.

Alternatively, this method can compare the first measurement with the theoretical value for the second measurement.

For example, if the first measurement is in the following ranges: 10.285 volts (V) to 12V, 8.571V to 10.285V, 6.857V to 8.571V, 5.142V to 6.857V, 3.428V to 5.142V, 1.714V to 3.428V , Or 0V to 1.714V and the second measurement should represent a binary value such as 001, 011, 010, 110, 111, 101, 100, respectively.

If this is not true, the rate of change is assumed to be zero.

If true, the rate of change is equal to the rate of change corresponding to the value of the first or second measurement. For example, such a rate of variability may be equal to the rate of change corresponding to the value of the first measurement, in which case the second measurement serves to monitor the system.

Thus, independently from the embodiment, the processor unit may apply at least one relation stored in the processor unit to compare the second measurement with the first measurement. A relational expression may take the form of one or more mathematical relational expressions or may in fact have the form of a table of values, for example.

In another aspect, the method may include positioning the mean pitch of each blade of the propeller at a predetermined position when the emergency electric handling member is operated by the pilot.

In another aspect, the propulsion system may include at least one propeller having a plurality of variable pitch blades, and the propulsion system may include a pitch correction system for modifying the variable pitch, Wherein the method comprises modifying the pitch by applying the rate of change of the pitch.

BRIEF DESCRIPTION OF THE DRAWINGS The present invention and its advantages will become more apparent from the following description of a given embodiment of the examples given with reference to the accompanying drawings, in which: Fig.
Figs. 1 to 5 are views showing the electric control device of the present invention. Fig.
6 is a diagram of an aircraft of the present invention.
7 is a diagram illustrating flight controls of an aircraft;
8 is a view for explaining a method of the present invention.

Elements present in two or more drawings are given the same reference numerals for each of them.

Fig. 1 shows an electric control device 1. Fig.

The electric control device (1) has a supporting body (2) for carrying the operating means (3). This operating means 3 is connected to the support 2 by means of an attachment system which gives freedom of movement to the operating means 3 with respect to the support 2. [

For example, the operating means 3 may include a control wheel rotatable about an operating axis AX that is stationary relative to the support 2. [ The attachment system can be in the form of a rod 200 that is secured to such a wheel and carried by bearings fixed to the support 2. [

Such a wheel may have a circumference provided with grip means to facilitate movement of a person by an act of manipulation. Such a wheel may be of the type described in document FR2984004.

Further, the electric control apparatus 1 may be provided with a return system 4. [ Such a return system 4 serves to drive the operating means 3 to a reference position called the " neutral " position POS1.

For example, such return system 4 may include at least one spring 5 or at least one gas actuator.

Figure 2 shows the rotary operating means (3). Such operating means 3 comprise an element 300 circumferentially held between two movable ends of the two springs 501, 502 of the return system.

The first spring 501 thus extends in a first direction DIR1 across the arc from the seat 250 secured to the support 2 to the first movable end 503. The second spring 502 is moved in a second direction DIR2 opposite the first direction DIR1 across the arc from the seat 250 secured to the support 2 to the second movable end 503, .

In addition, the return system 4 includes a pedestal 505. The pedestal 505 has a first contact surface suitable for interrupting the extension of the first spring 501 in the first direction DIR1 by interference with the first moveable end 503 and the second moveable end 504 in the second direction DIR2 to block the extension of the second spring 502 in the second direction DIR2. For example, such a pedestal has the form of a shoulder of the support 2.

This pedestal is also positioned coincident with the position at which the element 300 reaches the neutral position.

Therefore, after the operating member rotates in the second direction DIR2, the element 3 tends to compress the first spring 501. [ When the pilot no longer exerts any force on the operating member 3, even if the second spring 502 fails, the first spring 501 extends the operating member 3 in its neutral position Because it stops turning the operating member when the first movable end 503 reaches the pedestal 505. In this way,

Conversely, after the operating member has moved in the first direction DIR1, the element 3 tends to compress the second spring 502. [ When the pilot no longer exerts any force on the operating member 3, even if the first spring 501 fails, the second spring 502 extends the operating member 3 to its neutral position Because it stops turning the operating member when the second movable end 504 reaches the pedestal 505. [

In another aspect, and with reference to Figure 1, the electrical control device 1 may comprise a holding system 6. The function of the holding system 6 is to have the tendency to hold the operating means 3 at at least one position relative to the support 2, which is called the " index " position.

Specifically, the operating means 3 may be located at a plurality of individual indexed switch positions different from the neutral position. In this case, the holding system 6 tends to hold the operating means 3 at each switch position.

Referring to FIG. 3, a person moves the operating means 3 from the neutral position POS1 to the current position POS2, in order to command the system, such as the propulsion system of the aircraft.

In this case, in this example, the operating means 3 turns by an angle 100 around its operating axis AX.

The angular position of the operating means 3 relative to the neutral position determines the command given to the system by the electrical control device 1. [

The return system 4 returns the operating means 3 to the neutral position POS1 when the person hands off the operating means 3. [ If the return system malfunctions, the holding system tends to keep the operating means in the position it reached.

In the example of Figure 1, the retention system 6 may have the form of a friction system. For example, such a friction system may comprise a resilient member 7 that tends to push against the shoe 8 against a member forced to rotate with the operating means 3.

Alternatively, a notched system such as a system comprising a bearing ball and housings disposed in the ring of the operating means 3 can be envisaged. The resilient member then tends to place the ball in the housing.

Referring to Fig. 1, the electric control apparatus 1 includes two measuring means, each of which measures the position of the operating means.

Therefore, the electric control apparatus 1 has a first measuring system 10 which takes a first measurement indicating the current position of the operating means 3. The first measurement system 10 is attached to the support 2.

Further, the electric control apparatus 1 also has a second measuring system 20 which takes a second measurement indicating the current position POS2.

The first measurement system 10 and the second measurement system 20 are independent and dissimilar. In that case, each measurement system makes measurements independently of the other measurement systems.

For example, the first measurement system 10 comprises means for delivering a first measurement system in the form of a first signal S1 of analog type.

As shown in Figure 1, such a first measurement system 10 includes a potentiometer 11 integrated in an electronic circuit 12. The movement of the operating means 3 leads to a change in resistance of the potentiometer 11. [ In such a situation, the electronic circuit 12 carries the first measurement M1 in the form of a first electrical signal S1 having a voltage dependent on the position of the operating means 3.

For example, the first measurement M1 may be carried out as a function of the position of the operating means 3 and therefore in the following ranges as a function of the position of the movable terminal of the potentiometer 11: 10.285 V to 12 V, (S1) representing a voltage present in each of one of 10.285V, 6.857V to 8.571V, 5.142V to 6.857V, 3.428V to 5.142V, 1.714V to 3.428V, or 0V to 1.714V .

As an alternative to the potentiometer, the first measurement system may include a Hall effect sensor or RVDT.

In addition, the second measurement system 20 can deliver a second measurement M2, which is not of an analog type but has the form of a second signal S2 closer to that of the digital type. This second measuring system 20 is attached to the support 2.

For example, the second measurement system 20 includes a code wheel 21. The second measurement system 20 also includes a processor system 22 cooperating with the code wheel 21 to determine a current binary value corresponding to the current position POS2.

The code wheel 21 is forced to rotate with the operating means 3. For example, the code wheel may have the shape of the body of the wheel of the operating means. Such a body may include angular perforations for generating binary values.

In such a situation, the processor system may include one sensor 25, 26 per light beam generator 23, 24, one light beam generator 23, 24, and a calculation unit 27. Figure 1 shows two light beam generators. However, a processor system may have one light beam generator per signal bit that needs to be created.

When the beam reaches the sensor through one hole, the processor system may give a value of 1, which is the corresponding bit in the second measurement. Conversely, if no holes are configured to match the beam so that it does not reach the sensor, the processor system may give the corresponding bit a value of zero.

For example, the second measurement M2 may be a function of the position of the operating means 3 and the second signal having a binary value of 3 bits, such as 001, 011, 010, 110, 111, 101 or 100, S2).

To analyze the measurements, the electrical control device 1 comprises a processor unit 30.

The processor unit 30 may have a first signal S1 carrying a first measurement M1 and a second measurement M2 and an input 31 receiving a second signal S2.

In addition, the processor unit 30 may have at least one output for sending the control signal ORD to the system. In addition, and for example, the processor unit 30 may include a processor 32 that executes instructions stored in the memory 33.

Advantageously or additionally, the processor unit may comprise an integrated circuit, a programmable system or a logic circuit, and these examples are not limited to the categories given in the term " processor unit ".

Regardless of the embodiment, the processor unit 30 serves to compare the second measurement M2 and the first measurement M1 to generate the control signal ORD.

The processor unit 30 causes the operating means 3 to be in the neutral position POS1 when the first measurement and the second measurement do not both correspond to the same position of the operating means, presumably within some threshold tolerance. In this case, the processor unit generates a predetermined control signal (ORD) corresponding particularly to the neutral position.

Conversely, when the first measurement and the second measurement correspond to the same special position with respect to the operating means 3, the processor unit generates a predetermined control signal ORD that corresponds to such a particular position.

1, the processor unit is located outside the first assembly provided with the support 2 and the operating means 3 and also with the first and second measurement systems 10 and 20 .

Unlike the operating means 3, the first measuring system 10 and the second measuring system 20, the processor unit 30 is not attached to the support 2. The processor unit is therefore away from the first assembly.

In such a situation, the first measurement system 10 and the second measurement system 20 may be connected to at least one bus 36 leading, for example, to the processor unit 30 in particular. Such a bus 36 may be a CAN bus.

For example, the processor unit 30 is part of the computer 86 of the autopilot system that controls the pitch of the blades 83 of at least one propeller 800.

4, the first measurement system 10 and the second measurement system 20 are connected to a plurality of processor units 30, for example.

4 shows an architecture with two control devices 151 and 152 for use by, for example, pilots and copilot, respectively.

Each control device has a first measuring means 10, a second measuring means 20, and a processor unit 30. Such a processor unit may comprise a computer.

For example, such a computer may be a dual computer with two channels. Each of the channels has its own microprocessor. One of the two channels may serve to generate an instruction (COM) that may be suppressed as a result of detecting a mismatch as a result of communication with the first channel and the second channel.

In such a situation, each measuring means 10, 20 is connected to each of the processor units by two channels. The connections shown are wired connections, but they may include buses, and in particular CAN buses.

The processor units may also be interconnected.

In the second variant of Figure 5, the processor unit 30 is part of the first assembly, since it is attached to the support 2. For example, the processor unit 30 may take the form of a field programmable gate array (FPGA) logic circuit.

Therefore, the processor unit 30 is connected to the first measurement system 10 and the second measurement system 20. The processor unit 30 may also be connected to a system to be controlled by at least one bus 35, for example a CAN bus. For example, the processor unit 30 is connected to at least one computer 86 of an autopilot system that controls the pitch of the blades 83 of at least one propeller 800 by at least one CAN bus.

For example, with a duplex architecture, the processor unit 30 can be connected to two computers 86 by two CAN buses, each of which cooperates with a monitoring unit.

The processor unit 30 may also be connected to the dual computer 86 by two channels. Although it is possible to monitor between two computers in a dual architecture, it can occur between two dual channels of a single computer.

Moreover, the processor unit sends a control signal to each computer 86 via a respective bus 35. However, the processor unit may also transmit the first measurement and the second measurement to the computer, or may in fact transmit the result of the comparison it performs to the computer. Therefore, such a computer can prove that the control signal ORD sent is correct by making the same comparison with the processor unit.

Referring to FIG. 6, the electric control device 1 of the present invention may be disposed in a rotorcraft aircraft, that is, a rotary rotor 50.

The rotary wing 50 has a moving body 52. The moving body 52 extends vertically from the tail 54 to the nose 53 along the roll axis AXROL. The body also extends transversely along the pitching axis AXTANG from a first flank called "left" flank for convenience to a second flank called "right" flank 55 for convenience. Finally, the body extends heightwise from the bottom surface 58 toward the upper surface 57 along the yaw axis AXLAC.

The roll axis AXROL and the yaw axis AXLAC together define a vertical front-rear direction symmetry plane of the rotary wing 1.

Usually, the landing gear can project downwardly from the bottom surface 58 of the fuselage.

The rotor blade has a rotor blade (60) including at least one main rotor (61). The main rotor 61 is placed on the upper surface 57 of the body 52. The main rotor 61 is provided with a plurality of blades 52 connected to, for example, a hub 63. For convenience, the blades 62 are referred to as " main " blades.

The main rotor rotates around an axis called the " main " axis of rotation (AXROT), at least partially to at least partially contribute to providing lift and possibly propulsion to the rotor blade. The main axis of rotation may be stationary relative to the body 52.

The rotary wing 1 may also have a propulsion system 80 that provides an additional longitudinal thrust P to contribute to moving the rotor. Propulsion system 80 may tend to push or pull the rotor blades.

The propulsion system 80 may include at least one propeller 800 having a plurality of variable pitch blades 83.

For example, such a rotor blade has a lifting surface 70 that extends substantially transversely on either side of the shell. The lift surface 70 may include, for example, a left half-wing 71 extending from the left flank 56 and a right half-wing 72 extending from the right flank 55 .

The lift surface has a propeller 800 called a "first" propeller 81 and a propeller 800 called a "second" propeller 82. For example, the left half-wing 71 has a first propeller 81 and the right half-wing 72 has a second propeller 82. Thus, the first propeller 81 and the second propeller 82 are disposed transversely opposite the surface 52.

Each propeller produces a respective thrust force (P1, P2), which together generate an additional thrust (P). The first thrust P1 generated by the propeller 81 may be different from the second thrust P2 generated by the second propeller 82 in order to control yaw motion of the rotary wing.

The rotary wing 1 also has a power plant 75 for driving the first propeller 81, the second propeller 82 and the main rotor 60.

Such a power plant 75 includes at least one end 76 and a drive train connecting the engine to the first propeller 81, the second propeller 82 and the main rotor 60 .

For example, the drive train includes a main power transmission gear box (MGB) 77 having a rotor mast that drives the rotation of the main rotor. Such an MGB may also be connected to a first power transmission train 78 that rotates and drives the first propeller 81. Likewise, such an MGB may be connected to a second power transmission train 79 that rotationally drives the second propeller 82.

Other architectures can be envisioned.

Referring to FIG. 7, the rotary wing 50 has a plurality of flight controls (contol) for controlling the movement of the rotary wing.

Specifically, the pitch of the blades of the main rotor can be modified collectively and periodically.

For example, the rotor blade has a set of swash plates 65 including a non-rotating swashplate 66 and a rotating swash plate 67. The non-rotating swash plate 66 is connected to at least three actuators, referred to as " main " actuators 69, of the servo control type. A rotary swash plate 67 is connected to each of the blades 62 of the main rotor via a respective pitch rod 68.

In such a situation, the rotor blade may include a collective pitch lever 91. This collective pitch lever 91 can be pivoted in the rotational direction ROT1 around the pivot axis AXBASCU to control the main actuators in the same manner.

In addition, the rotor blade unit may include a cyclic stick 92. The cyclic stick 92 is pivoted in the rotational direction ROT3 around the second axis and in the rotational direction ROT2 about the first axis to control the main actuators in a different manner in order to control the attitude of the rotational wing. can do.

In addition, the pitch of the blades 83 of each of the propellers 800 can be modified by the pitch correction system 850.

By way of example, the pitch correction system 850 for the propeller may include a hydraulic valve 84 that supplies hydraulic pressure to the actuator. The actuator can be arranged in the hub of the propeller by means of an elongated shaft with perforations. The hydraulic valve 84 may be controlled by a power transmission train including, for example, an electric actuator 85. [ The electric actuator can be controlled by the computer 86. [

The pedal 93 may communicate with the computer 86 to control yaw motion of the aircraft by a thrust difference between a first thrust exerted by the first propeller and a second thrust exerted by the second propeller .

To control the magnitude of the additional thrust, the electric control device 1 of the present invention can be used. For example, the operating means 3 can be arranged in the collective pitch lever 91. [

In such a situation, the control signal sent by the electric control apparatus 1 may be a signal for controlling the rate of change of the additional thrust. When the pilot manipulates the manipulating means 3, the electric control device 1 requires a variation of the additional thrust at a rate of variation which can be either negative or positive. The computer 86 then instructs the pitch correction system 850 of the propellers to apply this rate of change and to modify the pitch of the blades of the propellers.

For example, the computer applies at least one mathematical relationship or obtains information from the database to generate commands to modify the pitch of the propeller blades to match the pitch variation requested by the electrical control device 1. [

Specifically, positioning the pitch of the propellers is accomplished by first generating a control signal transmitted to the computer 86, and secondly servo-controlled through a position sensor that measures information about the pitch of the blades . Such a position sensor may be connected to the computer 86. Further, such a position sensor can be placed very close to the blades, for example, at the hydraulic valve 84. [ The computer 86 then controls the electrical actuator 85 to follow the control signal received about the information returned by the position sensor.

In addition, the aircraft 50 may include an emergency electrical handling member 40 connected to the propulsion system 80. For example, the emergency electrical operating member 40 may have the form of a push button connected to the computer 86.

In another aspect, the aircraft 50 may include an emergency mechanical handling member 45 connected to the propulsion system. Such an emergency mechanical operating member 45 may include, for example, a lever for moving the electrical actuator 85.

Figure 8 shows a method implemented by an aircraft.

During the first step STP1, the operating means 3 can be manipulated by a person to cause a correction to an additional thrust.

During the first measurement step STP11, the first measurement system generates a first measurement M1. During the second measurement step STP12, the second measurement system generates a second measurement M2.

During the comparison step STP2, the first measurement and the second measurement are compared with each other.

In one embodiment, during the first stage (STP21) of the comparison step STP2, a first rate of variability associated with a variation in the additional thrust corresponding to the first measurement is calculated as a first variance Lt; / RTI >

During the second stage (STP22) of the comparison step (STP2), a second regression rate related to the variation of the additional thrust corresponding to the second measurement is determined by using a second relationship giving the second rate of variance as a function of the second measurement do.

Thereafter, the comparison is made by comparing the first variation rate and the second variation rate during the comparison stage STP23. This comparison makes it possible to determine whether the first measurement and the second measurement correspond to the same measured position with respect to the operating means 3 at the same time, or whether the first measurement and the second measurement do not correspond to the same position.

During the third step STP3, a thrust variation rate is generated to control the additional thrust P as a function of the position of the operating means 3 with respect to the reference.

Such a rate of change is generated as a function of the " measured " position of the operating means 3 when the first measurement and the second measurement simultaneously correspond to the measured position, When it does not correspond, it is adjusted to zero.

If appropriate, the rate of change generated to control the additional thrust (P) is equal to the value of the first rate of change and second rate of change, if the first rate of change is equal to the second rate of change.

On the other hand, when the first fluctuation rate is not equal to the second fluctuation rate, the rate of change generated to control the additional thrust P is equal to zero.

During the thrust correction step STP5, the variation rate provided during the third step STP3 is transmitted to the propulsion system to control the magnitude of the additional thrust. Where appropriate, a step of modifying the pitch of the blades of the propellers is carried out by applying said rate of variation.

This method may also include positioning (STP4) the average pitch of the blades of the propellers at a predetermined position when the emergency electric handling member 40 is operated by the pilot.

Of course, the invention can be embodied in many variations in its implementation. Although some embodiments have been described, it will be readily understood that it is not conceivable to suggest all possible embodiments without departing from the scope of the invention. It is therefore of course possible to consider replacing any of the described means with equivalent means without departing from the scope of the invention.

Claims (17)

An electric control device (1) having an operating means (3) and a supporting body (2)
Characterized in that said operating means (3) can be moved relative to said support (2), said operating means (3) being intended to be moved relative to said support (2) by a person, And a first measurement system (10) for making a first measurement of the current position (POS2) of the operating means (3) with respect to the position,
The electric control device 1 comprises a second measuring system 20 for making a second measurement of the current position POS2 and the first measuring system 10 and the second measuring system 20 are independent and resemble And a processor unit (30) for comparing the first measurement and the second measurement to generate a control signal (ORD) as a function of the current position (POS2), wherein the processor unit (30) And the operating means (3) is regarded as being in the neutral position (POS1) when the first measurement and the second measurement do not correspond to the same position with respect to the operating means. The method according to claim 1,
Wherein the first measurement system (10) comprises means for delivering a first measurement in the form of a first signal (S1) of analog type, the second measurement system (20) ≪ / RTI > in the form of a second measurement. The method according to claim 1,
The first measurement system (10) includes a potentiometer or Hall effect sensor or an active electrical sensor for sensing rotational movement, the first measurement being represented in the form of a first signal indicative of a voltage dependent on the current position, controller. The method according to claim 1,
The second measuring system 20 comprises a code wheel 21 forced to rotate with the operating means 3 and a code wheel 21 for determining the current binary value corresponding to the current position POS2, (22), the second measurement being represented in the form of a second signal (S2) comprising a binary value. The method according to claim 1,
The electrical control device (1) comprises a return system (4) which tends to return the operating means (3) to a neutral position (POS1). 6. The method of claim 5,
The return system (4) comprises a first spring (501) and a second spring (502) each provided with a first movable end (503) and a second movable end (504) ) Has an element disposed circumferentially between a first movable end (503) and a second movable end (504), the return system (4) comprising a pedestal (505), the first spring 501 tend to move circumferentially the first movable end 503 against the pedestal 505 in a first direction DIR1 to position the operating member 3 in the neutral position, The second spring 502 tends to move the second movable end 504 circumferentially against the pedestal 505 in the second direction DIR2 to position the operating member in the neutral position Electric control device. The method according to claim 1,
Characterized in that the electric control device (1) comprises a holding system (6) which tends to hold the operating means (3) in at least one " indexed & controller. The method according to claim 1,
The electrical control device 1 provides a first assembly provided with a support 2 together with an operating means 3 and a first and a second measuring system 10 and 20, 1 assembly and is secured to the support 2 and the processor unit 30 is for connecting to at least one computer 86 that is physically independent of the first assembly and the processor unit 30 ) Sends a control signal (ORD) to the computer (86), the control signal (ORD) being a parameter of a value established as a function of the measured position when both the first measurement and the second measurement correspond to the measured position (POS1) when said first measurement and said second measurement do not correspond to the same position. The method according to claim 1,
The electrical control device 1 provides a first assembly provided with a support 2 together with an operating means 3 and a first and a second measuring system 10 and 20, Wherein the processor unit is remote from the first assembly and the processor unit is connected to the first assembly by at least one bus, Is connected to a first measurement system (10) and a second measurement system (20), the control signal (ORD) being established as a function of the measured position when both the first measurement and the second measurement correspond to the measured position (POS1) when the first measurement and the second measurement do not correspond to the same position. An aircraft (50) having at least one main rotor (61)
The main rotor 61 at least partially contributes to providing lift to the aircraft 50 and the aircraft 50 includes at least one propulsion system 80 that is separate from the main rotor 61, The propulsion system 80 generates a thrust referred to as an " additional " thrust P to contribute at least in part to causing the aircraft 50 to advance, and the aircraft 50 is at least partially driven by an additional thrust P (1) connected to said propulsion system (80), said control signal (ORD) being connected to an additional thrust (P) transmitted to said propulsion system (80) Aircraft that requests a rate of change on the aircraft. 11. The method of claim 10,
The propulsion system 80 includes at least one propeller 800 having a plurality of variable pitch blades 83 and the propulsion system 80 includes a pitch correction system 850 for modifying the pitch, Wherein the processor unit (30) is coupled to the pitch correction system (850). 11. The method of claim 10,
Wherein the aircraft (50) comprises an emergency electrical handling member (40) connected to the propulsion system (80). 11. The method of claim 10,
Wherein the aircraft (50) comprises an emergency mechanical operating member (45) connected to the propulsion system. A method for controlling an aircraft propulsion system according to claim 10,
- generating a first measurement and a second measurement;
Comparing the first measurement and the second measurement; And
Generating a rate of change for controlling an additional thrust (P) as a function of the position of the operating means (3) relative to the reference (POS1)
The rate of change is generated as a function of the " measured " position of the operating means (3) when the first measurement and the second measurement correspond to the simultaneously measured position, And is set to 0 when it does not correspond to the same position. 15. The method of claim 14,
The step of comparing the first measurement with the second measurement may comprise the following stages:
Determining a first rate of change corresponding to the first measurement by using a relationship giving a first rate of change as a function of the first measurement;
Determining a second rate of change corresponding to the second measurement by using a relationship giving a second rate of change as a function of the second measurement; And
- comparing the first rate of variance with the second rate of variance. 15. The method of claim 14,
The propulsion system comprising at least one propeller,
The method includes positioning an average pitch with respect to the blades of the propeller at a predetermined position when the emergency electric handling member (40) is operated by a pilot. 15. The method of claim 14,
The propulsion system (80) includes at least one propeller (800) having a plurality of variable pitch blades (83), wherein the propulsion system (800) includes a pitch correction system for modifying the pitch, Is the rate of change relative to the pitch of the blades (83) of the propeller (800), and wherein the method comprises modifying the pitch by applying the rate of change.

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