A high-lift system airfoil position solution method and apparatus

Abstract

The application provides a high-lift system airfoil position calculation method and device, the method comprising: obtaining flap position sensor information and flap position sensor rotation number; obtaining actual movement stroke of the flap position sensor according to the flap position sensor rotation number, the flap position sensor information and zero offset of the flap position sensor; obtaining the flap position according to the actual movement stroke of the flap position sensor; the obtaining of the flap position sensor rotation number comprises: obtaining the angle difference between two continuous pictures according to a preset sampling frequency; when the angle difference indicates positive polarity change, adding 1 to the flap position sensor rotation number; when the angle difference indicates negative polarity change, subtracting 1 from the flap position sensor rotation number; otherwise, keeping the flap position sensor rotation number unchanged. The method can be compatible with flap position sensors of other types.

Description

Technical Field

[0001] This invention belongs to the field of high-lift systems and relates to a method and apparatus for calculating the wing surface position of a high-lift system. Background Technology

[0002] The high-lift system measures the flap / slat deflection angle using position sensors mounted on the wingtip. These angle measurement sensors include sine and cosine sensors, potentiometers, angular displacement sensors, and encoders. Because sine and cosine sensors have advantages such as high demodulation accuracy, high reliability, and strong environmental adaptability, they are mainly selected as flap / slat position sensors in the design of high-lift systems both domestically and internationally.

[0003] Different aircraft high-lift systems require different flap / slat position sensors due to variations in flap / slat travel and actuator travel. The main difference between flap / slat position sensors across different aircraft models lies in their reduction ratios, while the sensor's electrical characteristics remain consistent. If the flap / slat travel of the high-lift system is large, the corresponding transmission system travel is also large, necessitating a high reduction ratio for the flap / slat position sensor. The goal is to ensure that the sensor's travel across the entire flap / slat travel does not exceed 359°.

[0004] The design of flap / slat position sensors with high reduction ratios results in large sensor weight and size, which can even affect onboard structural installation. Furthermore, since different flap / slat position sensors are required for each aircraft model's high-lift system, the design of new products necessitates related functional, performance, and environmental testing, increasing system development costs.

[0005] How to calculate the wing surface position of a high-lift system is a key technology in the design of a high-lift system. Summary of the Invention

[0006] This invention proposes a method and apparatus for calculating the wing surface position of a high-lift system, which is compatible with other types of flap position sensors. Specifically, for the development of high-lift systems for new aircraft models, it is no longer necessary to design a separate flap position sensor; other types of flap position sensors or similar off-the-shelf products can be used, and flap position detection can be achieved by modifying the software program of the high-lift computer. This method ensures the accuracy of flap position detection and effectively shortens the project development cycle while reducing development and maintenance costs.

[0007] The first aspect of this invention provides a method for calculating the wing surface position of a high-lift system, comprising: Acquire flap position sensor information and flap position sensor rotation count. ; Based on the number of rotations of the flap position sensor flap position sensor information and flap position sensor zero offset Using formula Obtain the actual movement distance of the flap position sensor. ; Based on the actual movement distance of the flap position sensor Obtain the flap position; Among them, the number of rotations of the flap position sensor The acquisition includes: The angle difference between two consecutive frames is obtained according to the preset sampling frequency; When the angle difference indicates a positive polarity change, increment the number of rotations of the flap position sensor by 1; when the angle difference indicates a negative polarity change, decrement the number of rotations of the flap position sensor by 1; otherwise, keep the number of rotations of the flap position sensor unchanged.

[0008] Optionally, the direction of flap extension is positive, and the direction of flap retraction is negative.

[0009] Optionally, after obtaining the flap position, the method further includes: Rotate the flap position sensor a certain number of times flap position sensor zero offset It is stored in non-volatile memory.

[0010] Optionally, the method further includes: When powered on, check if the control handle is in the 0 position. If not, troubleshoot the control handle. After troubleshooting, the system needs to be powered on again.

[0011] Optionally, the method further includes: When the control handle is in the 0 position, determine the number of flap position sensor rotations stored in the non-volatile memory. If the value is 0, then report a "stick and rudder inconsistency" CAS alarm and invalidate the flap control handle command validity judgment flag.

[0012] Optionally, the method further includes: Upon power-up, based on information from the flap position sensor... And the flap position sensor zero-point bias stored in non-volatile memory and the number of rotations of the flap position sensor Using formula Obtain the actual movement distance of the flap position sensor. ; Based on the actual movement distance of the flap position sensor , to obtain the flap position.

[0013] Optionally, the method further includes: The number of flap position sensor rotations stored in non-volatile memory. When the value is 0, determine whether the flap position is within the preset range; If not, report a "stick and rudder inconsistency" CAS alarm and invalidate the flap control handle command validity check flag.

[0014] Optionally, the method further includes: When it is detected that ground maintenance personnel moved the control handle from position 0 to position 1 and then returned it to position 0, the flap control handle command validity check flag is set to valid. Control the flaps to extend and retract according to their position until they are fully retracted, thus clearing the "stick and rudder inconsistency" CAS alarm.

[0015] A second aspect of the present invention provides an apparatus for calculating the wing surface position of a high-lift system, for performing the method as described in any one of the first aspects.

[0016] This invention proposes a method and apparatus for calculating the wing surface position of a high-lift system. The beneficial effects of this invention include: (1) The present invention has high product versatility. That is, for the selection of flap or slat position sensors for new high-lift systems, it is not necessary to redesign flap / slat position sensors with corresponding reduction ratios. Instead, flap / slat position sensors that have been applied in other models can be selected, and different stroke positions can be detected through algorithms.

[0017] (2) The present invention can unify the configuration of flap / slat position sensors for subsequent high-lift systems, thereby reducing the complexity and cost of product configuration management.

[0018] (3) This invention can use shelf products, eliminating the need to develop new products, reducing system development costs and shortening the project development cycle.

[0019] (4) This invention can be extended to other rotating actuation systems such as hatch position detection. Attached Figure Description

[0020] Figure 1 A flowchart illustrating the method for calculating the wing surface position of a high-lift system; Figure 2 Logic diagram for processing the flap position after power-on; Figure 3 This relates to the control handle position, flap position, and the stroke of the rotary actuator. Detailed Implementation

[0021] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings: This invention proposes a method for calculating the wing surface position in a high-lift system. First, the system design inputs and motion polarity definitions are defined. Then, a high-lift computer identifies the positive and negative polarity changes of the flap position sensor and calculates the multi-turn motion distance of the flap position sensor based on a designed method. The flap position is then calculated using a lookup table. Finally, addressing the issue that the flap may be in any position after power-on restart, and the high-lift computer cannot identify the specific flap position using only the position sensor, a corresponding maintenance operation method and computer power-on processing logic are designed to ensure the flaps retract completely to the 0° position and allow the system to enter normal mode. The algorithm design flowchart is shown below. Figure 1 As shown.

[0022] I. System Design Input Definition (1) Flap position sensor (FPSU) reduction ratio The flap position sensor can be a rack-mount product, with a specified FPSU reduction ratio of [missing information]. .

[0023] (2) Rotary actuator (GRA) reduction ratio The specified reduction ratio of the rotary actuator is: .

[0024] (3) The relationship between the control handle position, flap position, and rotary actuator stroke. Adjust the control lever positions and flap positions. Rotary actuator travel stroke The relationship between them is as follows Figure 3 As shown.

[0025] II. Definition of Motion Polarity The direction of flap extension is defined as positive, and the direction of flap retraction is defined as negative. That is, moving the control lever from the low position to the high position is a positive operation, and vice versa is a negative operation; When the joystick is operated in the positive direction, the high-lift computer (FSECU) should issue a positive speed command; when the joystick is operated in the negative direction, the high-lift computer should issue a negative speed command.

[0026] III. Calculation of Total Travel of Transmission Line System (1) Calculation of the total stroke of the transmission shaft Total stroke of the drive shaft for: (1) (2) Total travel distance of flap position sensor Total travel distance of flap position sensor for: (2) IV. Method for Calculating the Movement Stroke of the Flap Position Sensor Define the left flap position sensor information collected in real time by the high-lift computer as: The real-time acquisition of information from the right flap position sensor is as follows: .

[0027] The actual movement distance of the left flap position sensor The current value of the left flap position sensor Subtract the zero-point offset of the left flap position sensor The calculation formula can be expressed as: (3) Actual movement of the right flap position sensor Current value of the right flap position sensor Subtract the zero-point offset of the right flap position sensor The calculation formula is as follows: (4) Left / right flap position sensor stroke change This can be uniformly expressed as the actual value of the current flap position sensor minus the flap position sensor offset. The calculation formula can be expressed as: (5) V. Design of the counting rules for the number of rotations of the flap position sensor For long-stroke flap systems, if the flap position sensor's deceleration ratio is small, it will inevitably result in the flap position sensor's rotation count being greater than 1. Therefore, the high-lift computer should configure a variable to count the number of rotations of the flap position sensor. .

[0028] The flap deployment is defined as positive, meaning that during flap deployment, the angle value of the flap position sensor continuously increases from a small value. When the flap position sensor angle value changes from its maximum value of 359° to 0°, it is recorded as one positive polarity change. The high-lift computer increments the flap position sensor's rotation count variable by 1. When the high-lift computer determines that a second positive polarity change has occurred, then... The forward counting method for the flap position sensor follows the same logic.

[0029] The retraction of the flaps is defined as negative, meaning that during flap deployment, the angle value of the flap position sensor continuously decreases from a large value. When the angle value of the flap position sensor changes from a minimum of 0° to 359°, it is recorded as one negative polarity change. The high-lift computer decrements the count variable of the flap position sensor's rotation by 1. When the high-lift computer determines that a second negative polarity change has occurred, then... The negative counting method for the flap position sensor follows the same logic.

[0030] During the flap retraction and extension process, if the flap position sensor first shows one positive polarity change and then one negative polarity change, the number of rotations of the flap position sensor is expressed as: .

[0031] VI. Calculation of the movement stroke of the flap position sensor Based on the calculation method for the movement stroke of the flap position sensor and the counting rules for the number of rotations, the formula for calculating the actual movement stroke of the left flap position sensor is as follows: (6) in, This represents the number of rotations of the left flap position sensor.

[0033] The formula for calculating the actual travel distance of the right flap position sensor is as follows: (7) in, This represents the number of rotations of the right flap position sensor.

[0034] VII. System Mechanical Zero Adjustment and Electrical Zero Adjustment (1) System mechanical zeroing operation After the flap system is initially installed on the aircraft, it needs to be moved to the fully retracted position with the help of ground support equipment before the high-lift system is powered on. If the flap system components are replaced, mechanical zeroing is required.

[0035] (2) Electrical zeroing After completing the mechanical zeroing of the high-lift system, ground maintenance personnel perform electrical zeroing using testing equipment. The ground maintenance personnel issue an electrical zeroing command through the testing equipment, and the high-lift computer should automatically read the actual positions of the left and right flap position sensors. , and the position of the left flap As the zero-point offset of the left flap position sensor, that is: (8) The high-lift computer will determine the position of the right flap. As the zero-point offset of the right flap position sensor, that is: (9) After electrical zeroing is completed, the high-lift computer stores the zero-offset values ​​of the left flap position sensor and the right flap position sensor into the non-volatile memory NVM.

[0036] (3) Calculation of the initial position of the flap After completing the electrical zeroing of the high-lift system, the initial position of the high-lift computer flaps. Set to 0, that is .

[0037] The high-lift computer needs to store the initial flap position in non-volatile memory (NVM).

[0038] 8. Calculation of actual flap position The actual flap position during system power-on and flap movement is as follows: Figure 3 The table in the table is used for lookup calculations, and the calculation formula can be expressed as: (1) Calculate the position of the left flap : (10) (2) Calculate the position of the right flap : (11) (3) Calculate the flap position (12) IX. Flap Position Information Storage If a flap position sensor-based counting algorithm is used, the main problem is that after each power outage and restart, the computer can only recognize the current flap position sensor angle value, but cannot identify the corresponding flap position. To solve this technical problem, the high-lift computer is required to store the following real-time data in non-volatile memory (NVM) during each instruction cycle: 1) Number of rotations of the flap position sensor That is, including , ; 2) Zero offset of left flap position sensor ; 3) Right flap position sensor zero offset ; 4) Initial position of flaps

[0039] 10. Operating Procedures Before Powering On the System Before each power-on, ground maintenance personnel / pilots should first check whether the FSCL (handle position) is in the 0 position. If it is in the 0 position, the high lift computer can be powered on normally. If the FSCL is not in the 0 position, the maintenance personnel should first move the FSCL to the 0 position before powering on the high lift computer.

[0040] XI. Power-on flap position processing logic The logic for handling the flap position after power-on is as follows: Figure 2 As shown.

[0041] (1) Information reading and acquisition of high-lift system after power-on After the system is powered on, the high-lift computer should read the following information: a) Number of rotations of the flap position sensor ; b) Zero offset of flap system , ; c) Initial position of the flaps ; d) The current actual gear position of the control lever; e) Current actual position of the left flap ; f) Current actual position of the right flap ; (2) Calculation of actual flap position The high-lift computer calculates the actual flap position according to the actual flap position calculation method. .

[0042] (3) Flange zero position judgment (a) The high-lift computer first determines whether the control handle is in the 0 position. If it is in the 0 position, it proceeds to the next logical judgment; otherwise, it performs a fault check on the control handle. After the fault check is completed, the system needs to be powered on again.

[0043] (b) The high-lift computer subtracts the initial position of the flap from the current actual position of the flap. If the absolute value of the difference is less than 0.5° and If the actual flap position is determined to be fully retracted, the system enters normal operating mode. The calculation formula is as follows: If | |<0.5° and ; Then it is determined that the flaps are currently in the fully retracted position; Otherwise, the high-lift calculation will report a "stick-rudder inconsistency" CAS alarm, and at the same time, the flap control handle command validity judgment flag will be set to invalid. And wait for ground maintenance personnel to intervene.

[0044] Interventional procedures include: S1. Ground maintenance personnel move the FSCL from position 0 to position 1 and then back to position 0. At this time, the high-lift computer sets the flap control handle command validity check flag to valid, i.e. .

[0045] S2. The high-lift computer calculates the actual movement distance of the left flap position sensor according to formula (6). The actual movement of the right flap position sensor is calculated according to formula (7). .

[0046] The high-lift computer then calculates the required flap angle based on formulas (10), (11), and (12). The command is given to control the flaps to retract and extend until they are fully retracted.

[0047] S3. When the high-lift computer determines that the flaps have moved to the fully retracted position, it will clear the "stick and rudder inconsistency" CAS alarm and put the system into normal mode.

[0048] This invention provides a method for calculating the wing surface position of a high-lift system, comprising: an algorithm design process, which first requires defining the system design input, then defining the motion polarity, calculating the total travel of the transmission system, designing the system's mechanical and electrical zeroing procedures, designing the method for calculating the travel of the flap position sensor, designing the counting rules for the number of motion cycles of the flap position sensor, calculating the travel of the flap position sensor, calculating the initial power-on position and actual operating position of the flap, designing the flap position information storage, designing the operation method before system power-on, and finally designing the computer processing logic after power-on.

[0049] The system design input definitions include: the reduction ratio definition of the flap position sensor, the reduction ratio definition of the rotary actuator, and the relationship between the control handle position and the flap position and the rotary actuator travel distance.

[0050] The definition of motion polarity includes: the direction of flap extension is positive, and the direction of flap retraction is negative. That is, moving the control handle from the low position to the high position is a positive operation, and vice versa; when the control handle is moved positively, the high lift computer (FSECU) should issue a positive speed command; when the control handle is moved negatively, the high lift computer should issue a negative speed command.

[0051] This invention can be applied to leading-edge slat systems, door actuation systems, and other similar rotary actuation systems.

Claims

1. A method for calculating the wing surface position of a high-lift system, characterized in that, include: Obtain flap position sensor information and flap position sensor rotation number FPSU_r; Based on the number of rotations of the flap position sensor FPSU_r, the flap position sensor information FPSU_CURRENT_POS, and the flap position sensor zero offset FPSU_BIAS, the actual movement stroke ΔFPSU_POS of the flap position sensor is obtained using the formula ΔFPSU_POS=FPSU_CURRENT_POS-FPSU_BIAS+360°×FPSU_r. The flap position is obtained based on the actual movement stroke ΔFPSU_POS of the flap position sensor; The acquisition of the flap position sensor rotation number FPSU_r includes: The angle difference between two consecutive frames is obtained according to the preset sampling frequency; When the angle difference indicates a positive polarity change, increment the number of rotations of the flap position sensor by 1; when the angle difference indicates a negative polarity change, decrement the number of rotations of the flap position sensor by 1; otherwise, keep the number of rotations of the flap position sensor unchanged. After obtaining the flap position, the method further includes: Store the number of rotations of the flap position sensor FPSU_r and the zero-position offset of the flap position sensor FPSU_BIAS in non-volatile memory; The formula for calculating the actual flap position during system power-on and flap movement is as follows: Flap position F pos =( L_F pos + R_F pos ) / 2; Among them, the left flap position L_F pos The calculation formula is L_F pos =ΔL_ FPSU _POS×F POS4 / θ fpsu Right flap position R_F pos The calculation formula is R_F pos =ΔR_ FPSU _POS×F POS4 / θ fpsu ;θ fpsu ΔL_FPSU_POS represents the total travel distance of the flap position sensor; ΔR_FPSU_POS represents the actual travel distance of the left flap position sensor; and ΔR_FPSU_POS represents the actual travel distance of the right flap position sensor.

2. The method for calculating the wing surface position of a high-lift system according to claim 1, characterized in that, Deploying the flaps in the direction of movement is positive, while retracting the flaps in the direction of movement is negative.

3. The method for calculating the wing surface position of a high-lift system according to claim 1, characterized in that, The method further includes: When powered on, check if the control handle is in the 0 position. If not, troubleshoot the control handle. After troubleshooting, the system needs to be powered on again.

4. The method for calculating the wing surface position of a high-lift system according to claim 3, characterized in that, The method further includes: When the control handle is in position 0, check if the number of flap position sensor rotations FPSU_r stored in the non-volatile memory is 0. If not, report a "stick and rudder inconsistency" CAS alarm and invalidate the flap control handle command validity check flag.

5. The method for calculating the wing surface position of a high-lift system according to claim 4, characterized in that, The method further includes: Upon power-up, based on the flap position sensor information FPSU_CURRENT_POS, and the flap position sensor zero-position bias FPSU_BIAS and flap position sensor rotation number FPSU_r stored in the non-volatile memory, the actual movement stroke ΔFPSU_POS of the flap position sensor is obtained using the formula ΔFPSU_POS=FPSU_CURRENT_POS-FPSU_BIAS+360°×FPSU_r. The flap position is obtained based on the actual movement distance ΔFPSU_POS of the flap position sensor.

6. The method for calculating the wing surface position of a high-lift system according to claim 5, characterized in that, The method further includes: When the number of flap position sensor rotations FPSU_r stored in the non-volatile memory is 0, determine whether the flap position is within the preset range; If not, report a "stick and rudder inconsistency" CAS alarm and invalidate the flap control handle command validity check flag.

7. The method for calculating the wing surface position of a high-lift system according to claim 4 or 6, characterized in that, The method further includes: When it is detected that ground maintenance personnel moved the control handle from position 0 to position 1 and then returned it to position 0, the flap control handle command validity check flag is set to valid. Control the flaps to extend and retract according to their position until they are fully retracted, thus clearing the "stick and rudder inconsistency" CAS alarm.

8. A device for calculating the wing surface position of a high-lift system, characterized in that, Used to perform the method as described in any one of claims 1-7.

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