1. A slat manipulation instruction determination method for a high lift system of an aircraft, the high lift system comprising:

a first flap control computer having a first flap channel and a first slat channel that are independent of each other;

a second flap control computer having a second flap channel and a second slat channel that are independent of each other;

a slat manipulating handle configured to be operable to a plurality of different handle detents, wherein each handle detent corresponds to an effective angular interval of the slat manipulating handle;

a first sensor, a second sensor, a third sensor, and a fourth sensor configured to independently measure an angular position of the slat joystick and generate sensor signals indicative of the measured angular position;

wherein the four first, second, and third channels are each communicatively connected to one of the four sensors and configured to acquire the sensor signals from one of the four sensors;

characterized in that the slat manipulation instruction determination method comprises determining an open-ground state of the aircraft, and,

in the event that the aircraft is determined to be in an airborne state, performing by each channel the following airborne decision steps:

judging whether the acquired sensor signal can meet an air effective clamping condition, wherein the air effective clamping condition is defined as that the angle position represented by the sensor signal falls into one effective angle interval and reaches a preset first time length threshold;

if the air effective clamping condition is met, a clamping instruction signal is determined based on the sensor signal and sent to the other three channels, and if the air effective clamping condition is not met, an invalid signal is generated and sent to the other three channels;

judging whether the card position instruction signal determined by the channel meets the matching condition, wherein the matching condition is defined as that any card position instruction signal consistent with the card position instruction signal determined by the channel is contained in three signals sent to the channel by the other three channels;

if the matching condition is met, judging the consistent clamping instruction signal as a system instruction, and sending the system instruction to the other three channels;

if the matching condition is not met, sequentially judging whether the determined clamping instruction signals meet the matching condition according to the priority sequence of the same opposite channel, the adjacent channel on the same side and the adjacent channel on the opposite side, judging the consistent clamping instruction signals as the system instruction when the matching condition is met, and sending the system instruction to the other three channels;

if the system command cannot be generated after the air judgment step is continuously executed for a plurality of times, the channel enters a failure-safety state, or if the system command cannot be generated after the air judgment step is executed within a preset second time threshold, the channel enters the failure-safety state.

2. The slat manipulation instruction determination method according to claim 1, further comprising:

in the event that the aircraft is determined to be in a ground state, performing by each channel the following ground determination steps:

judging whether the acquired sensor signal can meet a ground effective clamping condition, wherein the ground effective clamping condition is defined as that an angle position represented by the sensor signal falls into one effective angle interval and reaches a preset second duration threshold;

if the ground effective clamping condition is met, a clamping instruction signal is determined based on the sensor signal and sent to the other three channels, and if the ground effective clamping condition is not met, a channel fault signal is generated and sent to an engine display and unit warning system and the other three channels;

judging whether the card position instruction signal determined by the channel meets the matching condition;

if the matching condition is met, judging the consistent clamping instruction signal as a system instruction, and sending the system instruction to the other three channels;

and if the matching condition is not met, generating the channel fault signal and sending the channel fault signal to an engine display and unit warning system and the remaining three channels.

3. The slat steering command determining method according to claim 2, wherein, of the four sensors, the second sensor and the third sensor are two-channel sensors configured to measure and generate a first-path sensor signal and a second-path sensor signal, respectively;

the first slat channel and the second slat channel are configured to be capable of acquiring second path sensor signals of a third sensor and a second sensor respectively, the first flap channel is configured to be capable of acquiring a sensor signal of the first sensor as a main sensor signal and acquiring a first path sensor signal of the third sensor as a standby sensor signal, and the second flap channel is configured to be capable of acquiring a first path sensor signal of the second sensor as a main sensor signal and acquiring a sensor signal of the fourth sensor as a standby sensor signal.

4. The slat steering command determining method according to claim 2, wherein the four sensors are respectively two-channel sensors configured to be able to measure and generate a first sensor signal and a second sensor signal;

the first flap channel, the first slat channel, the second flap channel and the second slat channel are sequentially configured to respectively acquire a first sensor signal of the first sensor, a second sensor signal of the third sensor, a first sensor signal of the second sensor and a second sensor signal of the fourth sensor as main sensor signals, and respectively acquire a first sensor signal of the third sensor, a second sensor signal of the first sensor, a first sensor signal of the fourth sensor and a second sensor signal of the second sensor as standby sensor signals.

5. The slat manipulation instruction determining method according to claim 3 or 4, wherein, when the over-the-air determining step is performed by a channel configured to be able to acquire an active sensor signal and a standby sensor signal, determining whether the acquired sensor signal can satisfy an over-the-air effective detent condition is defined as determining whether at least one of the acquired active sensor signal and standby sensor signal can satisfy the over-the-air effective detent condition.

6. The slat manipulation instruction determining method according to claim 5, wherein, when the ground determining step is performed by a channel configured to be able to acquire a primary sensor signal and a backup sensor signal, determining whether the acquired sensor signals can satisfy a ground-effective-detent condition is defined such that the following conditions are satisfied at the same time:

the difference between the angular positions respectively represented by the acquired main sensor signal and the acquired standby sensor signal does not exceed a preset upper limit value of the angular difference;

the acquired angle positions respectively represented by the signals of the main sensor and the standby sensor fall into one effective angle interval to reach the second duration threshold.

7. A high lift system of an aircraft, the high lift system comprising:

a first flap control computer having a first flap channel and a first slat channel that are independent of each other;

a second flap control computer having a second flap channel and a second slat channel that are independent of each other;

a slat manipulating handle configured to be operable to a plurality of different handle detents, wherein each handle detent corresponds to an effective angular interval of the slat manipulating handle;

a first sensor, a second sensor, a third sensor, and a fourth sensor configured to independently measure an angular position of the slat joystick and generate sensor signals indicative of the measured angular position;

wherein the four first, second, and third channels are each communicatively connected to one of the four sensors and configured to acquire the sensor signals from one of the four sensors;

wherein the first slat control computer and the second slat control computer are configured to be able to determine an air-to-ground state of the aircraft, each channel being configured to be able to perform the following air decision step with the aircraft in an air state:

judging whether the acquired sensor signal can meet an air effective clamping condition, wherein the air effective clamping condition is defined as that the angle position represented by the sensor signal falls into one effective angle interval and reaches a preset first time length threshold;

if the air effective clamping condition is met, a clamping instruction signal is determined based on the sensor signal and sent to the other three channels, and if the air effective clamping condition is not met, an invalid signal is generated and sent to the other three channels;

judging whether the card position instruction signal determined by the channel meets the matching condition, wherein the matching condition is defined as that any card position instruction signal consistent with the card position instruction signal determined by the channel is contained in three signals sent to the channel by the other three channels;

if the matching condition is met, judging the consistent clamping instruction signal as a system instruction, and sending the system instruction to the other three channels;

if the matching condition is not met, sequentially judging whether the determined clamping instruction signals meet the matching condition according to the priority sequence of the same opposite channel, the adjacent channel on the same side and the adjacent channel on the opposite side, judging the consistent clamping instruction signals as the system instruction when the matching condition is met, and sending the system instruction to the other three channels;

if the system command cannot be generated after the air judgment step is continuously executed for a plurality of times, the channel enters a failure-safety state, or if the system command cannot be generated after the air judgment step is executed within a preset second time threshold, the channel enters the failure-safety state.

8. The high lift system of claim 7, wherein with the aircraft in a ground state, each channel is configured to be able to perform the following ground determination steps:

judging whether the acquired sensor signal can meet a ground effective clamping condition, wherein the ground effective clamping condition is defined as that an angle position represented by the sensor signal falls into one effective angle interval and reaches a preset second duration threshold;

if the ground effective clamping condition is met, a clamping instruction signal is determined based on the sensor signal and sent to the other three channels, and if the ground effective clamping condition is not met, a channel fault signal is generated and sent to an engine display and unit warning system and the other three channels;

judging whether the card position instruction signal determined by the channel meets the matching condition;

if the matching condition is met, judging the consistent clamping instruction signal as a system instruction, and sending the system instruction to the other three channels;

and if the matching condition is not met, generating the channel fault signal and sending the channel fault signal to an engine display and unit warning system and the remaining three channels.

9. The high lift system of claim 8, wherein the four sensors are each dual channel sensors configured to measure and generate a first sensor signal and a second sensor signal;

the first flap channel, the first slat channel, the second flap channel and the second slat channel are sequentially configured to respectively acquire a first sensor signal of the first sensor, a second sensor signal of the third sensor, a first sensor signal of the second sensor and a second sensor signal of the fourth sensor as main sensor signals, and respectively acquire a first sensor signal of the third sensor, a second sensor signal of the first sensor, a first sensor signal of the fourth sensor and a second sensor signal of the second sensor as standby sensor signals.

10. The high lift system of claim 9, wherein each passage is configured to determine whether at least one of the acquired primary and backup sensor signals is capable of meeting the air active detent condition when performing the air determination step, and to determine whether the following conditions are simultaneously met when performing the ground determination step:

the difference between the angular positions respectively represented by the acquired main sensor signal and the acquired standby sensor signal does not exceed a preset upper limit value of the angular difference;

the acquired angle positions respectively represented by the signals of the main sensor and the standby sensor fall into one effective angle interval to reach the second duration threshold.

Background

High lift systems for aircraft, especially for modern large aircraft, typically include slats located at the leading edge of the wing and flaps located at the trailing edge of the wing. The lift force of the airplane is provided by outwards extending the leading edge slat and the trailing edge flap and downwards bending to increase the wing area change configuration at the low-speed stages of takeoff, landing and the like of the airplane so as to ensure the reasonable sliding distance and safe takeoff speed of the airplane and improve the climbing rate, approach speed and approach attitude of the airplane at the same time.

Flap/Slat operating handles (collectively referred to as Flap/Slat Control Lever, FSCL for short) are commonly used in high lift systems to Control the extension and retraction of flaps and slats. The FSCL is typically mounted on a center console. The FSCL of the traditional structure mainly comprises a handle, a pull rod with a force sensing device, a planetary gear system, a four-way RVDT sensor and the like. The pilot first needs to lift the handle, which drives the pull rod to move along the slide rail (generally in the form of a slot). In the process, the force sensing device of the pull rod generates lifting force and friction force. The pull rod drives the gear train to rotate and drive the RVDT, so that an electric signal which can be analyzed by a Slat Control Computer (totally called a Slat-Flap Control Computer, SFCC for short) is generated.

The Flap Slat control computer is an important control element of high lift systems, and two SFCCs are usually installed on an aircraft, each of which includes 2 identical independent channels, namely one Flap Channel (Flap Channel) and one Slat Channel (Slat Channel). The two channels may be physically isolated from each other and if one SFCC fails, the slat and flap functions are still available, but will operate at half speed. The channel Control module of the slat Control computer generally consists of a Control branch (Control lane) and a monitor branch (monitor lane). The architecture of such a slat control computer as described above is shown, for example, in fig. 1. The communication connections between the various channels in the slat control computer are shown in fig. 1 specifically as being via a CAN bus communication connection, it being understood that this is also an inter-channel communication means to which embodiments of the invention described below are applicable.

However, one problem with the mechanisms of SFCC processing and selection of handle (i.e., steering device) commands in high lift systems of existing aircraft is that the redundant configuration employed by existing solutions, while generally available to some extent to ensure slat and flap functionality, will operate slat and flap functionality at half speed, such as operating slats and flaps of an aircraft at half speed, in the event that one SFCC fails or other problems exist involving steering commands. However, in some operating states of the aircraft, the operation of the slat and flap functions at half speed is not fully satisfactory for practical purposes, which makes the availability of high-lift systems less than fully guaranteed.

Accordingly, there is a need to provide a new slat manipulation instruction determination method for a high lift system of an aircraft and a high lift system of an aircraft to at least partially alleviate or solve the above-mentioned drawbacks and problems of the existing high lift systems of aircraft.

Disclosure of Invention

The invention provides a novel flap and slat operating instruction determining method for a high-lift system of an airplane and the high-lift system of the airplane, aiming at overcoming the defect that the usability of the high-lift system cannot be guaranteed to the fullest extent due to the defects of redundant configuration of the conventional high-lift system of the airplane and a handle instruction determining mechanism adopted by the conventional high-lift system of the airplane.

The invention solves the technical problems through the following technical scheme:

the invention provides a slat maneuver instruction determination method for a high lift system of an aircraft, the high lift system comprising:

a first flap control computer having a first flap channel and a first slat channel that are independent of each other;

a second flap control computer having a second flap channel and a second slat channel that are independent of each other;

a slat manipulating handle configured to be operable to a plurality of different handle detents, wherein each handle detent corresponds to an effective angular interval of the slat manipulating handle;

a first sensor, a second sensor, a third sensor, and a fourth sensor configured to independently measure an angular position of the slat joystick and generate sensor signals indicative of the measured angular position;

wherein the four first, second, and third channels are each communicatively connected to one of the four sensors and configured to acquire the sensor signals from one of the four sensors;

characterized in that the slat manipulation instruction determination method comprises determining an open-air state of the aircraft, and,

in the event that the aircraft is determined to be in an airborne state, performing by each channel the following airborne decision steps:

judging whether the acquired sensor signal can meet an air effective clamping condition, wherein the air effective clamping condition is defined as that the angle position represented by the sensor signal falls into one effective angle interval and reaches a preset first time length threshold;

if the air effective clamping condition is met, a clamping instruction signal is determined based on the sensor signal and sent to the other three channels, and if the air effective clamping condition is not met, an invalid signal (such as a null signal) is generated and sent to the other three channels;

judging whether the card position instruction signal determined by the channel meets the matching condition, wherein the matching condition is defined as that any card position instruction signal consistent with the card position instruction signal determined by the channel is contained in three signals sent to the channel by the other three channels;

if the matching condition is met, judging the consistent clamping instruction signal as a system instruction, and sending the system instruction to the other three channels;

if the matching condition is not met, sequentially judging whether the determined clamping instruction signals meet the matching condition according to the priority sequence of the same opposite channel, the adjacent channel on the same side and the adjacent channel on the opposite side, judging the consistent clamping instruction signals as the system instruction when the matching condition is met, and sending the system instruction to the other three channels;

if the system command cannot be generated after the air judgment step is continuously executed for a plurality of times, the channel enters a failure-safety state, or if the system command cannot be generated after the air judgment step is executed within a preset second time threshold, the channel enters the failure-safety state.

According to an embodiment of the invention, the slat manipulation instruction determination method further comprises:

in the event that the aircraft is determined to be in a ground state, performing by each channel the following ground determination steps:

judging whether the acquired sensor signal can meet a ground effective clamping condition, wherein the ground effective clamping condition is defined as that an angle position represented by the sensor signal falls into one effective angle interval and reaches a preset second duration threshold;

if the ground effective clamping condition is met, a clamping instruction signal is determined based on the sensor signal and sent to the other three channels, and if the ground effective clamping condition is not met, a channel fault signal is generated and sent to an engine display and unit warning system and the other three channels;

judging whether the card position instruction signal determined by the channel meets the matching condition;

if the matching condition is met, judging the consistent clamping instruction signal as a system instruction, and sending the system instruction to the other three channels;

and if the matching condition is not met, generating the channel fault signal and sending the channel fault signal to an engine display and unit warning system and the remaining three channels.

Based on such a preferred solution, a different design of the signal processing and decision logic is provided both in the aerial and in the terrestrial state, thereby providing the following two advantages. That is, on the one hand, it is sufficient to have reliability in most cases to operate the high-lift system of the aircraft at full speed, or at full speed rather than at half speed, based on the system commands, in the airborne state, and on the other hand, to be able to notify the engine display and crew warning system (EICAS for short) of the fault more timely in the ground state.

According to one embodiment of the present invention, the second sensor and the third sensor of the four sensors are two-channel sensors configured to measure and generate the first sensor signal and the second sensor signal, respectively;

the first slat channel and the second slat channel are configured to be capable of acquiring second path sensor signals of a third sensor and a second sensor respectively, the first flap channel is configured to be capable of acquiring a sensor signal of the first sensor as a main sensor signal and acquiring a first path sensor signal of the third sensor as a standby sensor signal, and the second flap channel is configured to be capable of acquiring a first path sensor signal of the second sensor as a main sensor signal and acquiring a sensor signal of the fourth sensor as a standby sensor signal.

According to one embodiment of the present invention, the four sensors are two-channel sensors configured to measure and generate a first sensor signal and a second sensor signal, respectively;

the first flap channel, the first slat channel, the second flap channel and the second slat channel are sequentially configured to respectively acquire a first sensor signal of the first sensor, a second sensor signal of the third sensor, a first sensor signal of the second sensor and a second sensor signal of the fourth sensor as main sensor signals, and respectively acquire a first sensor signal of the third sensor, a second sensor signal of the first sensor, a first sensor signal of the fourth sensor and a second sensor signal of the second sensor as standby sensor signals.

According to one embodiment of the present invention, when the over-the-air determining step is performed by a channel configured to be able to acquire an active sensor signal and a standby sensor signal, determining whether the acquired sensor signal can satisfy an over-the-air effective clamping condition is defined as determining whether at least one of the acquired active sensor signal and standby sensor signal can satisfy the over-the-air effective clamping condition.

According to one embodiment of the present invention, when the ground determination step is performed by a channel configured to be able to acquire the primary sensor signal and the backup sensor signal, determining whether the acquired sensor signals can satisfy the ground effective blocking condition is defined as satisfying the following conditions at the same time:

the difference between the angular positions respectively represented by the acquired main sensor signal and the acquired standby sensor signal does not exceed a preset upper limit value of the angular difference;

the acquired angle positions respectively represented by the signals of the main sensor and the standby sensor fall into one effective angle interval to reach the second duration threshold.

The invention also provides a high lift system for an aircraft, the high lift system comprising:

a first flap control computer having a first flap channel and a first slat channel that are independent of each other;

a second flap control computer having a second flap channel and a second slat channel that are independent of each other;

a slat manipulating handle configured to be operable to a plurality of different handle detents, wherein each handle detent corresponds to an effective angular interval of the slat manipulating handle;

a first sensor, a second sensor, a third sensor, and a fourth sensor configured to independently measure an angular position of the slat joystick and generate sensor signals indicative of the measured angular position;

wherein the four first, second, and third channels are each communicatively connected to one of the four sensors and configured to acquire the sensor signals from one of the four sensors;

characterized in that the first and second slat control computers are configured to be able to determine an open-ground state of the aircraft, each channel being configured to be able to perform the following in-air decision steps in the case of the aircraft being in an in-air state:

judging whether the acquired sensor signal can meet an air effective clamping condition, wherein the air effective clamping condition is defined as that the angle position represented by the sensor signal falls into one effective angle interval and reaches a preset first time length threshold;

if the air effective clamping condition is met, a clamping instruction signal is determined based on the sensor signal and sent to the other three channels, and if the air effective clamping condition is not met, an invalid signal is generated and sent to the other three channels;

judging whether the card position instruction signal determined by the channel meets the matching condition, wherein the matching condition is defined as that any card position instruction signal consistent with the card position instruction signal determined by the channel is contained in three signals sent to the channel by the other three channels;

if the matching condition is met, judging the consistent clamping instruction signal as a system instruction, and sending the system instruction to the other three channels;

if the matching condition is not met, sequentially judging whether the determined clamping instruction signals meet the matching condition according to the priority sequence of the same opposite channel, the adjacent channel on the same side and the adjacent channel on the opposite side, judging the consistent clamping instruction signals as the system instruction when the matching condition is met, and sending the system instruction to the other three channels;

if the system command cannot be generated after the air judgment step is continuously executed for a plurality of times, the channel enters a failure-safety state, or if the system command cannot be generated after the air judgment step is executed within a preset second time threshold, the channel enters the failure-safety state.

According to one embodiment of the invention, each channel is configured to be able to perform the following ground determination steps with the aircraft in a ground state:

judging whether the acquired sensor signal can meet a ground effective clamping condition, wherein the ground effective clamping condition is defined as that an angle position represented by the sensor signal falls into one effective angle interval and reaches a preset second duration threshold;

if the ground effective clamping condition is met, a clamping instruction signal is determined based on the sensor signal and sent to the other three channels, and if the ground effective clamping condition is not met, a channel fault signal is generated and sent to an engine display and unit warning system and the other three channels;

judging whether the card position instruction signal determined by the channel meets the matching condition;

if the matching condition is met, judging the consistent clamping instruction signal as a system instruction, and sending the system instruction to the other three channels;

and if the matching condition is not met, generating the channel fault signal and sending the channel fault signal to an engine display and unit warning system and the remaining three channels.

According to one embodiment of the present invention, the four sensors are two-channel sensors configured to measure and generate a first sensor signal and a second sensor signal, respectively;

the first flap channel, the first slat channel, the second flap channel and the second slat channel are sequentially configured to respectively acquire a first sensor signal of the first sensor, a second sensor signal of the third sensor, a first sensor signal of the second sensor and a second sensor signal of the fourth sensor as main sensor signals, and respectively acquire a first sensor signal of the third sensor, a second sensor signal of the first sensor, a first sensor signal of the fourth sensor and a second sensor signal of the second sensor as standby sensor signals.

According to one embodiment of the invention, each channel is configured to determine, when performing the air determination step, whether at least one of the acquired primary sensor signal and back-up sensor signal is capable of satisfying the air-critical condition, and, when performing the ground determination step, to determine whether the following conditions are simultaneously satisfied:

the difference between the angular positions respectively represented by the acquired main sensor signal and the acquired standby sensor signal does not exceed a preset upper limit value of the angular difference;

the acquired angle positions respectively represented by the signals of the main sensor and the standby sensor fall into one effective angle interval to reach the second duration threshold.

On the basis of the common knowledge in the field, the above preferred conditions can be combined randomly to obtain the preferred embodiments of the invention.

The positive progress effects of the invention are as follows:

according to the method for determining the operation instruction of the flap and the high lift system of the airplane, the flap/slat can be ensured to move safely and reliably at full speed as far as possible in the flight state, the flight safety is guaranteed, and the maintenance of the high lift system is facilitated.

Drawings

FIG. 1 is a schematic diagram of the architecture of a typical slat control computer.

Fig. 2 is a schematic block architecture diagram of a flap or slat channel control module in a flap control computer that can be specifically employed in a flap manipulation instruction determination method according to some preferred embodiments of the present invention.

Fig. 3 schematically illustrates the electrical connection of FSCL and SFCC involved in the slat manipulation instruction determination method according to some preferred embodiments of the present invention.

FIG. 4 schematically illustrates the electrical connection of the FSCL to the SFCC involved in a slat manipulation instruction determination method according to further alternative preferred embodiments of the present invention.

FIG. 5 is a schematic diagram of an instruction determination mechanism and processing logic involved in a slat manipulation instruction determination method according to some preferred embodiments of the present invention.

Detailed Description

The following detailed description of the preferred embodiments of the present invention, taken in conjunction with the accompanying drawings, is intended to be illustrative, and not restrictive, and it is intended that all such modifications and equivalents be included within the scope of the present invention.

In the following detailed description, directional terms, such as "left", "right", "upper", "lower", "front", "rear", and the like, are used with reference to the orientation as illustrated in the drawings. Components of embodiments of the present invention can be positioned in a number of different orientations and the directional terminology is used for purposes of illustration and is in no way limiting.

A method of determining slat manipulation commands for a high lift system of an aircraft according to a preferred embodiment of the invention is exemplified below. Wherein the high lift system comprises: a first flap control computer having a first flap channel and a first slat channel that are independent of each other; a second flap control computer having a second flap channel and a second slat channel that are independent of each other; a slat manipulating handle configured to be operable to a plurality of different handle detents, wherein each handle detent corresponds to an effective angular interval of the slat manipulating handle; a first sensor, a second sensor, a third sensor, and a fourth sensor, the four sensors configured to independently measure an angular position of the slat joystick and generate sensor signals indicative of the measured angular position.

Wherein the four first, second, and second flap channels are each communicatively connected to one of the four sensors and configured to be capable of acquiring a sensor signal from one of the four sensors.

The slat manipulation instruction determination method includes determining an air-ground state of the aircraft, and, in a case where it is determined that the aircraft is in the air state, executing the following air determination steps by each of the channels:

judging whether the acquired sensor signal can meet an air effective clamping condition, wherein the air effective clamping condition is defined as that the angle position represented by the sensor signal falls into an effective angle interval and reaches a preset first time length threshold;

if the air effective clamping condition is met, a clamping instruction signal is determined based on the sensor signal and sent to the other three channels, and if the air effective clamping condition is not met, an invalid signal (such as a null signal) is generated and sent to the other three channels;

judging whether the card position instruction signal determined by the channel meets the matching condition, wherein the matching condition is defined as that any card position instruction signal consistent with the card position instruction signal determined by the channel is contained in three signals sent to the channel by the other three channels;

if the matching condition is met, judging the consistent clamping instruction signal as a system instruction, and sending the system instruction to the other three channels;

if the matching condition is not met, sequentially judging whether the determined clamping instruction signals meet the matching condition according to the priority sequence of the same opposite-side channel, the adjacent same-side channel and the adjacent opposite-side channel, judging the consistent clamping instruction signals to be system instructions when the matching condition is met, and sending the system instructions to the other three channels;

if the system instruction cannot be generated after the air judgment step is continuously executed for a plurality of times, the channel enters a failure-safety state, or if the system instruction cannot be generated after the air judgment step is executed within a preset second time length threshold value, the channel enters the failure-safety state.

It is to be understood, however, that the present channel, the opposite side of the same channel, the same side of the adjacent channel, and the opposite side of the adjacent channel are understood with reference to the following table 1, i.e., the "opposite side" channel refers to a channel belonging to a different SFCC than the present channel, and the "adjacent" channel refers to the relationship between channels belonging to the same SFCC but corresponding to the flap channel and the slat channel, respectively.

More specifically, the flap or slat channel control module of the flap control computer referred to in this application may, for example, employ a modular architecture as shown in fig. 2.

According to some embodiments of the invention, the slat manipulation instruction determination method further comprises, in the event that the aircraft is determined to be in a ground state, performing, by each channel, the following ground determination steps:

judging whether the acquired sensor signal can meet a ground effective clamping condition, wherein the ground effective clamping condition is defined as that the angular position represented by the sensor signal falls into an effective angular interval and reaches a preset second time length threshold;

if the ground effective clamping condition is met, a clamping instruction signal is determined based on the sensor signal and sent to the other three channels, and if the ground effective clamping condition is not met, a channel fault signal is generated and sent to an engine display and unit warning system (namely EICAS) and the other three channels;

judging whether the card position instruction signal determined by the channel meets the matching condition;

if the matching condition is met, judging the consistent clamping instruction signal as a system instruction, and sending the system instruction to the other three channels;

if the matching condition is not met, a channel fault signal is generated and sent to an engine display and unit warning system (namely EICAS) and the remaining three channels.

Based on such a preferred solution, a different design of the signal processing and decision logic is provided both in the aerial and in the terrestrial state, thereby providing the following two advantages. That is, on the one hand, it is sufficient to have reliability in most cases to operate the high-lift system of the aircraft at full speed, or at full speed rather than at half speed, based on the system commands, in the airborne state, and on the other hand, to be able to notify the engine display and crew warning system (EICAS for short) of the fault more timely in the ground state.

According to some preferred embodiments of the present invention, two dual channel sensors and two single channel sensors are used in the four sensors. For example, among the four sensors, the second sensor and the third sensor are two-channel sensors configured to measure and generate the first sensor signal and the second sensor signal, respectively.

The first slat channel and the second slat channel are configured to be capable of acquiring second path sensor signals of a third sensor and a second sensor respectively, the first flap channel is configured to be capable of acquiring a sensor signal of the first sensor as a main sensor signal and acquiring a first path sensor signal of the third sensor as a standby sensor signal, and the second flap channel is configured to be capable of acquiring a first path sensor signal of the second sensor as a main sensor signal and acquiring a sensor signal of the fourth sensor as a standby sensor signal.

It will be appreciated that such a sensor arrangement as described above may optionally provide a redundant arrangement in terms of sensor signals for control of one of the flaps and slats.

According to alternative preferred embodiments of the present invention, all of the four sensors are dual-channel sensors capable of measuring and generating a first sensor signal and a second sensor signal, respectively. Correspondingly, the first flap channel, the first slat channel, the second flap channel, and the second slat channel are sequentially configured to respectively acquire a first sensor signal of the first sensor, a second sensor signal of the third sensor, a first sensor signal of the second sensor, and a second sensor signal of the fourth sensor as the primary sensor signals, and respectively acquire a first sensor signal of the third sensor, a second sensor signal of the first sensor, a first sensor signal of the fourth sensor, and a second sensor signal of the second sensor as the backup sensor signals.

Further preferably, when the over-the-air determination step is performed by a channel configured to be able to acquire the active sensor signal and the standby sensor signal, determining whether the acquired sensor signal can satisfy an over-the-air effective clamping condition is defined as determining whether at least one of the acquired active sensor signal and the standby sensor signal can satisfy the over-the-air effective clamping condition.

And, when the ground determination step is performed by a channel configured to be able to acquire the primary sensor signal and the backup sensor signal, determining whether the acquired sensor signal is able to satisfy the ground valid card condition is defined as satisfying the following conditions at the same time:

the difference between the angular positions respectively represented by the acquired main sensor signal and the acquired standby sensor signal does not exceed a preset upper limit value of the angular difference;

the acquired angle positions respectively represented by the main sensor signal and the standby sensor signal fall into an effective angle interval to reach a second duration threshold.

For example, and more particularly, when the ground determination step is performed by a channel configured to be able to acquire the primary sensor signal and the backup sensor signal, the following sub-steps may be performed:

judging whether the difference between the angle positions respectively represented by the acquired main sensor signal and the acquired standby sensor signal exceeds an angle difference upper limit value or not;

if the angle difference exceeds the upper limit value of the angle difference, generating a channel fault signal and sending the channel fault signal to an engine display and unit warning system (namely EICAS) and other channels;

if the angular difference does not exceed the upper limit value of the angular difference, judging whether the angular positions respectively represented by the acquired main sensor signal and the acquired standby sensor signal fall into an effective angular interval or not;

if the fault does not fall into the effective angle interval, generating a channel fault signal and sending the channel fault signal to an engine display and unit warning system (namely EICAS) and other channels;

if the angle position of the main sensor signal and the angle position of the standby sensor signal are within the effective angle interval, continuously monitoring whether the angle positions respectively represented by the acquired main sensor signal and the acquired standby sensor signal are always within the effective angle interval within a time period reaching a second duration threshold;

if the angle is always within the effective angle interval, determining consistent clamping instruction signals according to the angle positions respectively represented by the signals of the main sensor and the standby sensor, judging the clamping instruction signals as system instructions, and sending the system instructions to the other three channels;

if the main sensor signal or the standby sensor signal is detected to move out of the effective angle interval, a channel fault signal is generated and sent to an engine display and unit warning system (namely EICAS) and other channels.

Various aspects of the slat steering command determination method according to a preferred embodiment of the present invention will be illustrated in more detail below on the basis of a preferred embodiment in which all of the four sensors described above employ a dual channel RVDT sensor.

The electrical connection of the FSCL to the SFCC, which can also be understood as a communication connection and a signal transmission, is schematically shown in fig. 3, wherein the mechanical components can be understood as a slat steering handle, i.e. the rotational axis of the slat steering handle. Wherein, the handle's 4 binary channels RVDT produces 8 way RVDT position signals of handle simultaneously, and 8 way handle RVDT position signals send corresponding SFCC control channel and control passageway simultaneously.

FIG. 4 shows a simplified configuration of the 6-way handlebar RVDT signal corresponding to the two dual channels used in the four sensors described aboveSensor and two single channel sensor embodiments. Wherein the F1 channel receives the RVDT as shown in FIG. 4_A1、RVDT_C1Signal, S1 channel receive RVDT_C2Signal, F2 channel receive RVDT_B1、RVDT_D1Signal, S2 channel receive RVDT_B2A signal. Each flap channel has a redundant RVDT signal to ensure that the flap channel receives the handle command signal.

After the pilot moves the FSCL, 2 flap channels respectively receive the main RVDT and the standby RVDT signals, carry out synchronous processing according to the control logic, communicate with other three channels, and select the final correct system command through a matching mechanism. And each flap channel of the computer receives a two-redundancy handle instruction transmission mode, so that the flap system can be placed at the instruction position at full speed under special conditions of the airplane.

It should be appreciated that the various aspects of the slat steering command determination method referred to in the example shown in FIG. 4 are substantially the same as those described below in connection with the example shown in FIG. 3, and thus, the following detailed description will be made only for a preferred embodiment in which a dual channel RVDT sensor is employed for all four sensors.

Referring to FIG. 3, the FSCL sensor RVDT_A1、RVDT_C1Flap channel (hereinafter referred to as F1), RVDT, connecting SFCC1_A2、RVDT_C2Slat channel (S1) connected to SFCC1, handle sensor RVDT_B1、RVDT_D1Flap channel (hereinafter referred to as F2), RVDT, connecting SFCC2_B2、RVDT_D2The slat channel (hereinafter referred to as S2) of SFCC2 is connected.

Each channel of the SFCC receives two RVDT signals, and the priorities of the two RVDT signals (i.e. the main signal takes precedence over the standby signal) are shown in Table 2 below.

In this example, the handle RVDT electrical travel angle is 60 degrees, and the handle RVDT electrical travel angle is a function of the SFCC channel system commands as shown in Table 3 below. It should be understood, however, that the RVDT electrical travel angles for the different handle detents may be determined or set as appropriate.

In this embodiment described herein, the SFCC may first determine the current state of the aircraft based on, for example, the airspeed signal and the primary on-board signal. Wherein, only when the airspeed is less than 60knot and the WOW signal =1, judging that the aircraft is on the ground; otherwise, in order to ensure the safety of the airplane, when either the airspeed or the main wheel load is in an air state, the airplane is in the air by default. The logic for this determination of the open space condition is shown in table 4 below.

In this embodiment, the following SFCC control logic may be specifically configured.

If the SFCC determines that the aircraft is airborne based on either the airspeed signal (airspeed >60 kt) or the primary on-board signal (WOW = 0), the handle RVDT command signal may be processed by an interface FPGA in the SFCC and processed or controlled based on logic as illustrated in detail below, which may be referred to in fig. 5 in conjunction with fig. 2.

The processing and control logic of the control decision step portion will be described in detail below with reference to the left side portion of fig. 5.

a) Processing logic for RVDT signals

The SFCC channel monitors the electrical characteristics of the connected RVDT sensors, and the converted electrical stroke angle is logically judged as follows:

a.1, judging whether the electrical stroke angle of the main/standby RVDT signals is within an effective range of a certain clamping nominal value, wherein the effective range is preferably +/-1 degree (or +/-1.2 degrees or +/-1.5 degrees, and is determined according to the precision of the handle RVDT);

a.2 if the main RVDT signal is not within the valid range, using the backup RVDT signal, performing A.4; otherwise, executing A.3;

and A.3, if the main RVDT signal is in the effective range, judging whether the electric stroke is kept for a certain time in the effective range of the nominal value corresponding to a certain clamping position. This time is preferably 200 milliseconds;

and A.4, if the standby RVDT signal is in the effective range, judging whether the electric stroke is kept for a certain time in the effective range of the nominal value corresponding to a certain clamping position. This time is preferably 200 milliseconds;

a.5 if any RVDT signal meets the requirements of an effective range and a threshold time at the same time, the SFCC judges the RVDT signal to be an effective value and converts the RVDT signal into a new handle clamping instruction (0 clamping position, or 1 clamping position, or 2 clamping positions, or 3 clamping positions, or 4 clamping positions);

a.6 if neither RVDT signal satisfies the range and threshold time requirements, then the SFCC will choose a default value, preferably NULL;

a.7, the channel sends a new handle clamping position instruction or NULL to other three channels for comparison, and the channel executes the following judgment logic:

b) handle position clamping instruction processing logic

The computer channels communicate with each other, and a new handle clamping instruction generated by the channel is transmitted through a CAN bus (CCDL), and the processing logic of the part is described as follows:

b.1, if the channel is normal in function and the new handle clamping position instruction of at least one channel is the same as the channel, judging that the new handle clamping position instruction generated by the channel is effective, judging that the new handle clamping position instruction generated by the channel is a system instruction, and transmitting the system instruction to other three channels;

b.2, if the channel is normal in function, but the new handle clamping position instruction of the channel is not the same as the channel, judging that the new handle clamping position instruction generated by the channel is Invalid, transmitting an Invalid state (Invalid) to other three channels, and executing C.1;

b.3, if the channel is not normal in function, executing C.1;

c.1, if the 'new handle clamping position instruction' generated by the same channel on the opposite side is effective and the channel function is normal, judging that the received new handle clamping position instruction generated by the same channel on the opposite side is a 'system instruction' by the channel;

c.2, if the 'new handle clamping position instruction' generated by the same channel on the opposite side is invalid, executing D.1;

c.3 if the same channel on the opposite side is not normal in function, executing D.1;

d.1, if the 'new handle clamping position instruction' generated by the adjacent side channel is effective and the channel function is normal, judging that the received new handle clamping position instruction generated by the adjacent side channel is a 'system instruction' by the channel;

d.2, if the 'new handle clamping position instruction' generated by the adjacent side channel is invalid, executing E.1;

d.3, if the adjacent side channel is not normal in function, executing E.1;

e.1, if the 'new handle clamping position instruction' generated by the opposite side adjacent channel is effective and the channel function is normal, the channel judges that the received new handle clamping position instruction generated by the opposite side adjacent channel is a 'system instruction';

e.2, if the new handle clamping position instruction generated by the adjacent channel on the opposite side is invalid, executing F.1;

e.3, if the adjacent channel on the opposite side is not normal in function, executing F.1;

f.1, triggering a watchdog circuit, and enabling the channel to enter a failure-safety state;

g.1 if the channel is judged to be a system instruction, waiting for a time sequence with consistent coordination, and sending the system instruction to a corresponding PDU motor;

h.1 if no new handle position command can be obtained, the corresponding RVDT signal is read again;

h.2, if the new handle clamping position instruction can not be obtained for three times continuously, the channel enters a failure-safety state and does not send data outwards any more.

If the SFCC judges that the aircraft is on the ground according to the airspeed signal (the airspeed is less than 60knot) and the main wheel load signal (WOW = 1), the fault channel directly reports the fault of the channel, so that the maintenance of the crew is facilitated, and the probability of the aircraft with the fault flight is reduced. The logic for the interface FPGA in the SFCC to process the handle RVDT command signals is shown in the right part of figure 5.

Referring to the left hand side of fig. 5, the processing and control logic for the ground decision step section is detailed as follows:

a) RVDT signal processing logic

The SFCC channel monitors the electrical characteristics of the connected RVDT sensors, and the converted electrical stroke angle is logically judged as follows:

a.1, judging whether the electrical stroke angle difference of the main/standby RVDT signals is within a certain interval range (the interval range is preferably +/-1 degree);

a.2, if the difference value of the electrical stroke angles of the main/standby RVDT signals is not within the interval range, directly reporting the fault of the channel and transmitting an Invalid state (Invalid) to other three channels;

a.3, if the electrical stroke angle difference of the main/standby RVDT signals is within the interval range, executing A.4;

a.4, judging whether the electrical stroke angle of the main/standby RVDT signals is within an effective range of a certain clamping nominal value, wherein the effective range is preferably +/-1 degree (or +/-1.2 degrees or +/-1.5 degrees, and is determined according to the precision of the handle RVDT);

a.5, if any path of the main RVDT signal or the standby RVDT signal is not in the effective range, directly reporting the fault of the channel and transmitting an Invalid state (Invalid) to other three channels;

a.6, if the main RVDT signal and the standby RVDT signal are both in the effective range, judging whether the electric stroke is kept for a certain time (the time is preferably 200 milliseconds) in the effective range of the nominal value corresponding to a certain position;

a.7 if the main RVDT signal and the standby RVDT signal simultaneously meet the requirements of an effective range and a threshold time, the SFCC judges the RVDT signal to be an effective value and converts the RVDT signal into a new handle clamping instruction (0 clamping position, or 1 clamping position, or 2 clamping positions, or 3 clamping positions, or 4 clamping positions);

a.8 if any RVDT signal of the channel does not meet the requirements of the range and the threshold time, defaulting an Invalid state (Invalid) and directly reporting the fault of the channel;

a.9, the channel sends a new handle clamping position instruction or an Invalid state (Invalid) to other three channels for comparison, and the channel executes the following judgment logic:

b) handle position clamping instruction processing logic

The computer channels communicate with each other, and a new handle clamping instruction generated by the channel is transmitted through a CAN bus (CCDL), and the processing logic of the part is described as follows:

b.1, if the channel is normal in function and the new handle clamping position instruction of at least one channel is the same as the channel, judging that the new handle clamping position instruction generated by the channel is effective, judging that the new handle clamping position instruction generated by the channel is a system instruction, and transmitting the system instruction to other three channels;

b.2, if the channel is normal in function, but the new handle clamping position instruction of the channel is not the same as that of the channel, judging that the new handle clamping position instruction generated by the channel is Invalid, transmitting an Invalid state (Invalid) to other three channels, and directly reporting the fault of the channel;

b.3, if the function of the channel is abnormal, directly reporting the fault of the channel;

and B.4, if the channel is judged to be the system command, waiting for the time sequence with consistent coordination, and sending the system command to the corresponding PDU motor.

In summary, in this embodiment, the SFCC determines that the aircraft is in the air or on the ground according to the airspeed signal and the main wheel load signal. If the aircraft is in the air, executing the air instruction judgment logic, generating a system instruction according to the priority, wherein the EICAS does not display the current channel fault so as to ensure full-speed movement of flaps/slats and guarantee flight safety, but recording the channel fault condition in an NVM (Non-volatile memory) for facilitating subsequent maintenance; if the airplane is judged to be on the ground, the ground instruction judgment logic is executed, the channel fault is directly reported, and the slat fault can be displayed on the EICAS in real time, so that the maintenance of crew is facilitated, and the probability of the airplane with the fault flight is reduced.

Taking the F1 channel as an example, in the case of different faults (i.e., different sensor signal matching results), the setting manner of the logic judgment priority can be set as shown in table 5 below.

By the aid of the mode, when the aircraft is in an aerial state, no matter what kind of faults occur, as long as the RVDT sensor data of one handle is correct, a pilot can operate the FSCL to ensure that the FSCL can output effective and available command commands, and the high-lift system can operate at full speed without half speed in any aerial environment.

The two flap panel control computers are connected through an inter-computer Data Link (CBDL) and exchange Data with each other. The computers are connected by a Cross Channel Data Link (CCDL) and exchange Data with each other. The link may be a CAN bus, an ARINC429 bus or other type of digital bus.

Based on the processing logic in the above-described embodiment, after the pilot moves the slat manipulating handle, the 4 channels each receive the command signal of the handle, perform synchronous processing, and finally determine the correct system command to be executed through the voting mechanism with the processing logic as described above.

The SFCC channel is used as an F1 channel to illustrate the process of processing the handle command, and in this example, the conversion table of the RVDT electrical stroke angle of the handle and the system command shown in table 3 can be referred to for understanding.

For example, referring to table 3 above, when the pilot moves the slat handle from 0 to 2 positions, the RVDT sensor position output changes from-30 degrees to 0 degrees, which is collected by each of the four dual channel RVDT sensors and transmitted to the SFCC's interface FPGA.

The interface FPGA firstly judges whether the RVDT position signal is effective or not and is within a tolerance range, if the signal is not changed within a certain time period (preferably 200 milliseconds), the position signal is confirmed to be used as a basis for calculating a handle clamping instruction, the handle clamping instruction is processed into a new handle clamping instruction according to the table 1, and the new handle clamping instruction is communicated with other three channels through a CAN bus.

The F1 channel compares the new handle position command with the new handle position commands generated by the other three channels in subsequent time windows. At this time, there may be two cases that occur:

1) under normal conditions: if the channel F1 judges that the new handle clamping instruction is '2 clamping', and at least one of the other three channels judges that the new handle clamping instruction is '2' clamping, the handle clamping instruction is successfully matched, and the channel F1 considers that the generated new system instruction is valid, and generates a 'system instruction';

2) in the abnormal case: if the F1 channel judges that a new handle clamping instruction is ' 1 clamping ' or ' NULL ', the other three channels judge that a new handle clamping instruction is ' 2 clamping, if the SFCC judges that the airplane is in the air according to an airspeed signal (airspeed >60 kt) or a main wheel load signal (WOW = 0), the F1 channel preferably selects the instruction from the F2 channel as a ' system instruction ' according to control logic, the EICAS does not display flap half-speed fault so as to ensure flap full-speed movement and flight safety, but records the fault condition of the channel in the NVM, thereby facilitating subsequent maintenance; if the SFCC judges that the airplane is on the ground according to the airspeed signal (the airspeed is less than 60knot) and the main wheel load signal (WOW = 1), the EICAS displays a flap half-speed fault, and the F1 channel directly reports the fault of the channel, so that the maintenance of the crew is facilitated, and the probability of the airplane with the fault flight is reduced.

Finally, the F1 path converts the "system command" into a current command via internal logic processing. The four channels will issue respective current commands to the corresponding PDU motors in one and the same time sequence.

According to the invention, an embodiment of a high lift system of an aircraft can also be provided, wherein the high lift system comprises: a first flap control computer having a first flap channel and a first slat channel that are independent of each other; a second flap control computer having a second flap channel and a second slat channel that are independent of each other; a slat manipulating handle configured to be operable to a plurality of different handle detents, wherein each handle detent corresponds to an effective angular interval of the slat manipulating handle; a first sensor, a second sensor, a third sensor, and a fourth sensor, the four sensors configured to independently measure an angular position of the slat joystick and generate sensor signals indicative of the measured angular position.

Wherein the four first, second, and second flap channels are each communicatively connected to one of the four sensors and configured to be capable of acquiring a sensor signal from one of the four sensors.

Wherein the first and second slat control computers are configured to be able to determine an air-ground state of the aircraft, and each channel is configured to be able to perform a preset air decision step in a case where the aircraft is in the air state, and configured to be able to perform a preset ground decision step in a case where the aircraft is in the ground state. For specific configurations of the devices and control logic related to the air determination step and the ground determination step, reference may be made to the distance description made in the foregoing for each embodiment of the slat operation instruction determination method, and details are not repeated here.

While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.