CN109987250B - Adjustment detection system and adjustment detection method for movable wing surface of airplane - Google Patents
Adjustment detection system and adjustment detection method for movable wing surface of airplane Download PDFInfo
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- CN109987250B CN109987250B CN201910270249.7A CN201910270249A CN109987250B CN 109987250 B CN109987250 B CN 109987250B CN 201910270249 A CN201910270249 A CN 201910270249A CN 109987250 B CN109987250 B CN 109987250B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Abstract
The application discloses an aircraft movable airfoil surface adjustment detection system and an adjustment detection method, wherein the system comprises a signal adjustment box, a board card insertion box, a comprehensive control computer, a program-controlled power supply, a display and a matched cable, wherein the signal adjustment box is used for carrying out fault positioning and metering of the aircraft movable airfoil surface detection system, the matched cable is connected with the signal adjustment box, actuators on a wing and a tail wing and control surface position sensors, the board card insertion box is used for providing required excitation signals to condition working instructions and then drive the actuators to stretch and retract, the comprehensive control computer is used for sending operator instructions through a man-machine interaction interface, controlling the movement of the movable airfoil surface and feeding back the movement state of the airfoil surface to a software interface, and adjustment and detection of ailerons, spoilers, aileron position sensors, elevators and rudder and elevating position sensors are completed.
Description
Technical Field
The application relates to a technology for testing movable wing surfaces of an airplane, in particular to a system and a method for adjusting and detecting the movable wing surfaces in the assembly stage of airplane components.
Background
The fly wing surface of the aircraft is an airfoil surface which can be controlled by manipulation on a wing and a tail wing, and mainly comprises an elevator, an aileron, a rudder, a spoiler and the like, the fly-by-wire control system realizes the control of the gesture and the course of the aircraft by manipulating the deflection of each fly wing surface of the aircraft, and the change of tiny parameters on the airfoil surface can influence the flight gesture, so that the fly wing surface is an important component related to the flight safety of the aircraft.
Certain accumulated errors can be formed in the production stage of the aircraft due to factors such as manufacturing and assembly processes, and if the adjustment and detection work of the movable airfoil surface is not performed in the aircraft manufacturing stage, the power-on inspection result in the final assembly stage cannot be ensured to completely meet the technical requirements of various indexes of the airfoil surface in the aircraft design scheme. Although some aircraft adopts an aircraft wing surface automatic zeroing mechanism in the design of a flight control system, after the assembly work is finished, the movable wing surface is not required to be adjusted, and the aircraft wing surface automatic zeroing is directly carried out through the flight control system in the final assembly stage so as to offset part of installation errors, if the accumulated installation errors are overlarge and exceed the wing surface automatic zeroing range, the zero position adjustment of the control surface cannot be realized by the automatic zeroing mechanism of the flight control system, and the limit deflection angle which can be achieved by the wing surface cannot be ensured.
Therefore, in the assembly stage of the components of the wings and the tail wings of the aircraft, the deflection performance of the movable wing surfaces is required to be detected, test items comprise the neutral position of the control surface, the limit deflection angle of the control surface and the uniformity of the deflection process, the assembly size is continuously adjusted through the repeated iterative process of performance test, installation adjustment and performance test, and the accumulated error is reduced until the deflection performance of the wing surfaces reaches the allowable error range of the technical index, and the components can be delivered to the next stage of the production of the aircraft.
The existing method for adjusting and detecting the movable wing surface of the airplane mainly comprises the following steps: and adjusting and detecting the movable wing surface in the assembly stage of the wing and the tail wing of the airplane. Because only movable wing surfaces of wings and tail wings of an aircraft, actuators of all the movable wing surfaces, control surface position sensors and related computer finished products in a flight control system are installed in the partial installation stage, the movable wing surfaces cannot be adjusted and detected by using an electric transmission control mode, the actuators can only be in a damping working mode, and the control surfaces are deflected in a mode of manually loading external force. The second method is as follows: after the finished product of the flight control system and the airborne cable are completely installed, the movable airfoil surface adjustment detection is carried out by adopting an electric transmission control mode, if the movable airfoil surface adjustment detection is unqualified, the movable airfoil surface adjustment detection is returned to the assembly stage for reassembling, and then the assembly test is carried out, wherein the counter attack of the assembly step seriously affects the production and manufacturing progress of the aircraft.
Disclosure of Invention
Aiming at the problems in the prior art, the application aims to provide an adjusting and detecting system for an airplane movable airfoil surface.
The utility model provides an aircraft activity airfoil adjustment detecting system, including signal conditioning case, the integrated control computer, the programmable power supply, display and supporting cable, signal conditioning case back panel distributes has the socket array, through the cable of outfit and each airfoil actuator, control surface position sensor, signal cross-linking and adaptation are carried out between the integrated control computer, every socket is designed into error-proof socket and makes the silk screen printing sign, signal conditioning case's front panel distributes and links the piece array absolutely, signal conditioning case inside is equipped with the core pencil, introduce the signal of back panel to the disconnected piece of front panel on fault location and aircraft activity airfoil adjustment detecting system's measurement, supporting cable connects on the wing aileron actuator, spoiler actuator, aileron position sensor, accomplish aileron, adjusting and detecting of aileron position sensor, supporting cable connects the fin lifting rudder actuator, rudder lifting position sensor, accomplish the adjustment and the detection of elevator, rudder lifting position sensor; the board card plug-in box consists of an excitation board, a servo amplification board and a signal demodulation board, wherein the excitation board provides required excitation signals for an actuator of a tested airfoil and a control surface position sensor, the servo amplification board regulates a working instruction and then drives the actuator to move in a telescopic way, and the signal demodulation board demodulates an alternating current signal into a direct current signal and then synthesizes the direct current signal and the instruction signal to form closed-loop control; the comprehensive control computer runs test software which is matched with the display for use and is provided with a remote communication port, the test software comprises an airfoil adjustment detection module, a control surface position sensor detection module and a communication module, the airfoil adjustment detection module sends an operator instruction through a human-computer interaction interface, the movement of a movable airfoil is controlled, the movement state of the airfoil is fed back to a software interface, the adjustment detection test work of the movable airfoil of the aircraft is completed, the control surface position sensor detection module sends an electrifying instruction of the operator, and meanwhile, an output signal generated when the sensor moves is acquired and displayed, the detection test work of the control surface position sensor is completed, and the communication module realizes the communication between the movable airfoil adjustment detection system of the aircraft and a production site hydraulic oil source system and an deflection angle detection system, so that the overall arrangement and the safety protection of the operator in the test are facilitated; the programmable power supply is controlled by test software to be turned on or turned off and is used for providing working power supply for each test board card of the board card plug-in box and the signal conditioning box.
The test software is designed with a separation test mechanism, a limit protection mechanism and a power-off protection mechanism, wherein the separation test mechanism is used for only testing a single actuator of the airfoil to be tested each time, and the rest actuators of the airfoil to be tested are placed in a damping follow-up state, so that the force fighting problem during the adjustment and detection of the movable airfoil is solved; the limiting protection mechanism is used for simultaneously collecting the control surface position parameter of the external deflection angle detection system and the control surface position parameter of the patent, comprehensively comparing, and sending a stop instruction to stop the motion of the movable airfoil when any value reaches the deflection limit of the airfoil; if the operation instruction can not control the airfoil to stop in the movable airfoil surface adjustment and detection process, the airfoil has a trend of continuously deflecting towards the limit position, and a power-off protection mechanism is adopted to forcibly turn off the power supply, so that the movable airfoil surface is prevented from being damaged.
A method for aircraft movable airfoil deflection detection using the system, comprising the steps of:
step 1: after the assembly of the wing and tail wing parts of the aircraft is completed, connecting a signal regulating box with an aileron actuator, a spoiler actuator, an elevator actuator, a rudder actuator, an aileron position sensor and an elevator position sensor by using a matched cable, and connecting a network cable with a comprehensive computer, a hydraulic oil source system and a deflection angle detection system;
step 2: connecting a hydraulic pipeline with a hydraulic oil source system, an aileron actuator, a spoiler actuator, an elevator actuator and a rudder actuator;
step 3: the aircraft movable airfoil surface adjustment detection system and the deflection angle detection system are powered on and initialized normally, a hydraulic oil source system is started and adjusted to the working pressure, and the hydraulic oil source system and the deflection angle detection system are communicated with the aircraft movable airfoil surface adjustment detection system normally;
step 4: selecting a single actuator of a movable airfoil surface to be detected on test software, electrifying the actuator, enabling other actuators to be in a damping state, and electrifying a control surface position sensor;
step 5: transmitting a movable airfoil surface deflection instruction, reading the working parameter states of the movable airfoil surface actuator and the control surface position sensor, and analyzing the working parameter states into physical quantity meanings;
step 6: repeating the step 5, and sending deflection instructions of different positions of the movable airfoil surface;
step 7: sending a neutral position instruction of the movable airfoil, and after the airfoil is returned to the center, powering off the actuator and powering off a control surface position sensor;
step 8: judging whether the technical indexes tested in the steps 5 and 6 meet the design requirements, if not, closing a hydraulic oil source system, an aircraft movable airfoil surface adjustment detection system and an deflection angle detection system, reassembling and adjusting the airfoil surface or the actuator, repeating the steps 3, 4, 5, 6, 7 and 8 after adjustment until the technical indexes tested in the steps 5 and 6 meet the design requirements, and if the technical indexes tested in the steps 5 and 6 meet the design requirements, carrying out the test in the step 9;
step 9: and (3) selecting whether to continue testing other actuators of the movable airfoil surface to be detected, if so, repeating the steps 4, 5, 6, 7 and 8, otherwise, closing the hydraulic oil source system, the aircraft movable airfoil surface adjustment detection system and the deflection angle detection system, and ending the detection.
The application relates to a movable airfoil surface adjustment detection system used in the aircraft assembly stage, which has the beneficial effects that:
(1) The problem of relying on manual means to detect in the prior art is solved, the test condition of the aircraft wing surface is improved, the aircraft assembly and manufacturing period is shortened, and the aircraft production progress is ensured;
(2) The integrated level is high, and the integrated test system integrates the detection of the movable airfoil surface and the detection of the control surface position sensor of the airplane, has high automation level and is easy to operate and use;
(3) The test device has a perfect movable airfoil surface driving safety protection mechanism, and is safe and reliable in test.
Drawings
FIG. 1 is a block diagram of an adjustable airfoil adjustment and detection system for an aircraft
FIG. 2 is a schematic diagram of an embodiment of an adjustable airfoil for a wing
FIG. 3 is a schematic diagram of an embodiment of an adjustment detection of a movable wing surface of a tail wing
The numbering in the figures illustrates: the system comprises a movable wing surface adjustment detection system of an airplane, a display device 2, a signal adjustment box 3, a board card insertion box 4, a comprehensive control computer 5, a programmable power supply 6, a network cable 7, a matched cable 8, a hydraulic pipeline 9, an aileron 10, a spoiler 11, an elevator 12, a rudder 13, a wing 14 and a tail wing 15.
Detailed Description
As shown in fig. 1-3, the aircraft movable wing surface adjustment detection system 1 comprises a signal conditioning box 3, a board card plug-in box 4, a comprehensive control computer 5, a programmable power supply 6, a display 2 and a matched cable 8.
The rear panel of the signal conditioning box 3 is distributed with a socket array, signal crosslinking and adaptation are carried out between the signal conditioning box 3 and each wing surface actuator, a control surface position sensor, a board card plug-in box 4 and a comprehensive control computer 5 through a matching cable 8, each socket is designed into an error-proof socket and is used for silk-screen printing identification, the front panel of the signal conditioning box 3 is distributed with a broken connection block array, a core wire harness is arranged in the signal conditioning box, and signals of the rear panel are led into broken connection blocks of the front panel to facilitate fault positioning and metering of the aircraft movable wing surface adjustment detection system 1. The auxiliary cable 8 is connected with an aileron actuator, a spoiler actuator and an aileron position sensor on the wing 14, so that adjustment and detection of the aileron 10, the spoiler 11 and the aileron position sensor can be completed. The matching cable 8 is connected with the elevating rudder actuator, the rudder actuator and the elevating rudder position sensor of the tail wing 15, so that the adjustment and the detection of the elevating rudder 12, the rudder 13 and the elevating rudder position sensor can be completed.
The board card plug-in box 4 is composed of an excitation board, a servo amplification board and a signal demodulation board. The excitation plate provides required excitation signals for the actuator of the tested airfoil surface and the control surface position sensor, the servo amplification plate adjusts working instructions and then drives the actuator to stretch and retract, and the signal demodulation plate demodulates alternating current signals into direct current signals and then synthesizes the direct current signals and the command signals to form closed-loop control.
The integrated control computer 5 runs test software, is matched with the display 2 for use, and is provided with a remote communication port. The test software adopts a modularized design and comprises an airfoil surface adjustment detection module, a control surface position sensor detection module and a communication module. The wing surface adjustment detection module sends an operator instruction through a man-machine interaction interface, controls the movable wing surface to move, feeds back the movement state of the wing surface to a software interface, and completes the adjustment detection test work of the movable wing surface of the aircraft; the control surface position sensor detection module sends an energizing instruction of an operator, and simultaneously acquires and displays an output signal when the sensor moves, so as to complete the detection test work of the control surface position sensor; the communication module realizes the communication between the movable airfoil surface adjustment detection system 1 of the airplane and the hydraulic oil source system and the deflection angle detection system of the production site, and is convenient for the overall arrangement and the safety protection of operators in the test.
The test software is designed with a separation test, limit protection and power-off protection mechanism. The separation testing mechanism is that only a single actuator of the airfoil to be tested can be tested each time, and other actuators of the airfoil to be tested are placed in a damping follow-up state, so that the force fighting problem during the adjustment and detection of the movable airfoil is solved; the limiting protection mechanism is used for simultaneously collecting the control surface position of the external deflection angle detection system and the control surface position parameter of the patent, comprehensively comparing, and sending a stop instruction to stop the motion of the movable airfoil when any value reaches the deflection limit of the airfoil; if the operation instruction can not control the airfoil to stop in the movable airfoil surface adjustment and detection process and the airfoil has a trend of continuously deflecting towards the limit position, a power-off protection mechanism can be adopted to forcibly shut off the power supply, so that the movable airfoil surface is prevented from being damaged.
The programmable power supply 6 is controlled by test software to be turned on or turned off, and is used for providing working power supply for each test board card of the board card plug-in box 4 and the signal conditioning box 3.
The method for detecting the movable wing surface of the airplane by using the system comprises the following testing steps:
step 1: after the assembly of the airplane wings 14 and the tail wings 15 in the assembly stage is completed, connecting a matched cable 8 with a signal regulating box 3, an aileron actuator, a spoiler actuator, an elevator actuator, a rudder actuator, an aileron position sensor and an elevator position sensor, and connecting a network cable 7 with a comprehensive computer 5, a hydraulic oil source system and a deflection angle detection system;
step 2: connecting a hydraulic pipeline 9 with a hydraulic oil source system, an aileron actuator, a spoiler actuator, an elevator actuator and a rudder actuator;
step 3: the aircraft movable airfoil surface adjustment detection system 1 and the deflection angle detection system are powered on and initialized normally, a hydraulic oil source system is started and adjusted to the working pressure, and the hydraulic oil source system and the deflection angle detection system are communicated with the aircraft movable airfoil surface adjustment detection system 1 normally;
step 4: selecting a single actuator of a movable airfoil surface to be detected on test software, electrifying the actuator, enabling other actuators to be in a damping state, and electrifying a control surface position sensor;
step 5: transmitting a movable airfoil surface deflection instruction, reading the working parameter states of the movable airfoil surface actuator and the control surface position sensor, and analyzing the working parameter states into physical quantity meanings;
step 6: repeating the step 5, and sending deflection instructions of different positions of the movable airfoil surface;
step 7: sending a neutral position instruction of the movable airfoil, and after the airfoil is returned to the center, powering off the actuator and powering off a control surface position sensor;
step 8: judging whether the technical indexes tested in the steps 5 and 6 meet the design requirements, if not, closing a hydraulic oil source system, an aircraft movable airfoil surface adjustment detection system and an deflection angle detection system, reassembling and adjusting the airfoil surface or the actuator, repeating the steps 3, 4, 5, 6, 7 and 8 after adjustment until the technical indexes tested in the steps 5 and 6 meet the design requirements, and if the technical indexes tested in the steps 5 and 6 meet the design requirements, carrying out the test in the step 9;
step 9: and (3) selecting whether to continue testing the rest actuators of the movable airfoil surface to be detected, if so, repeating the steps 4, 5, 6, 7 and 8, otherwise, closing the hydraulic oil source system, the aircraft movable airfoil surface adjustment detection system 1 and the deflection angle detection system, and ending the detection.
Claims (1)
1. The method is characterized in that an aircraft movable wing surface adjustment detection system is used, the adjustment detection system comprises a signal adjustment box, a board card insertion box, a comprehensive control computer, a programmable power supply, a display and a matched cable, a socket array is distributed on the rear panel of the signal adjustment box, signal crosslinking and adaptation are carried out between the matched cable and each wing actuator, a control surface position sensor, the board card insertion box and the comprehensive control computer, each socket is designed into an error-proof socket and used for making a silk-screen mark, a broken connection block array is distributed on the front panel of the signal adjustment box, a core wire harness is arranged in the signal adjustment box, a signal of the rear panel is led into the broken connection block of the front panel for fault location and measurement of the aircraft movable wing surface detection system, the matched cable is connected with an aileron actuator, a spoiler actuator and an aileron position sensor on a wing, adjustment and detection of the aileron, the aileron position sensor and the rudder position sensor are completed, and the direction rudder is connected with the elevating rudder, the elevating rudder position sensor and the elevating rudder position sensor; the board card plug-in box consists of an excitation board, a servo amplification board and a signal demodulation board, wherein the excitation board provides required excitation signals for an actuator of a tested airfoil and a control surface position sensor, the servo amplification board regulates a working instruction and then drives the actuator to stretch and retract, and the signal demodulation board demodulates an alternating current signal into a direct current signal and then synthesizes the direct current signal and the instruction signal to form closed-loop control; the comprehensive control computer runs with test software matched with the display and is provided with a remote communication port, the test software comprises an airfoil adjusting and detecting module, a control surface position sensor detecting module and a communication module, the airfoil adjusting and detecting module sends an operator instruction through a man-machine interaction interface to control the movement of a movable airfoil and feeds the movement state of the airfoil back to a software interface to complete the adjustment and detection test work of the movable airfoil of the aircraft, the control surface position sensor detecting module sends the power-on instruction of the operator, and simultaneously collects and displays the output signal when the sensor moves to complete the detection test work of the control surface position sensor, and the communication module realizes the communication between the movable airfoil adjusting and detecting system of the aircraft and a hydraulic oil source system and a deflection angle detecting system of a production site, so that the overall arrangement and the safety protection of the operator in the test are facilitated; the programmable power supply is controlled to be turned on or turned off by test software, and is used for providing working power supply for each test board card and signal conditioning box of the board card plug-in box, the test software is designed with a separation test mechanism, a limit protection mechanism and a power-off protection mechanism, the separation test mechanism is that only a single actuator of the airfoil to be tested can be tested each time, and other actuators of the airfoil to be tested are placed in a damping follow-up state, so that the force fighting problem during the adjustment and detection of the movable airfoil is solved; the limiting protection mechanism is used for collecting control surface position parameters of an external deflection angle detection system at the same time, carrying out comprehensive comparison, and sending a stop instruction to stop the movement of the movable airfoil when any value reaches the deflection limit of the airfoil; if the operation instruction can not control the wing surface to stop in the adjustment and detection process of the movable wing surface, and the wing surface has a trend of continuously deflecting towards the limit position, the power supply is forcibly turned off by adopting a power-off protection mechanism, the movable wing surface is prevented from being damaged, and the adjustment and detection method by using the adjustment and detection system comprises the following steps:
step 1: after the assembly of the wing and tail wing parts of the aircraft is completed, connecting a signal regulating box with an aileron actuator, a spoiler actuator, an elevator actuator, a rudder actuator, an aileron position sensor and an elevator position sensor by using a matched cable, and connecting a network cable with a comprehensive computer, a hydraulic oil source system and a deflection angle detection system;
step 2: connecting a hydraulic pipeline with a hydraulic oil source system, an aileron actuator, a spoiler actuator, an elevator actuator and a rudder actuator;
step 3: the aircraft movable airfoil surface adjustment detection system and the deflection angle detection system are powered on and initialized normally, a hydraulic oil source system is started and adjusted to the working pressure, and the hydraulic oil source system and the deflection angle detection system are communicated with the aircraft movable airfoil surface adjustment detection system normally;
step 4: selecting a single actuator of a movable airfoil surface to be detected on test software, electrifying the actuator, enabling other actuators to be in a damping state, and electrifying a control surface position sensor;
step 5: transmitting a movable airfoil surface deflection instruction, reading the working parameter states of the movable airfoil surface actuator and the control surface position sensor, and analyzing the working parameter states into physical quantity meanings;
step 6: repeating the step 5, and sending deflection instructions of different positions of the movable airfoil surface;
step 7: sending a neutral position instruction of the movable airfoil, and after the airfoil is returned to the center, powering off the actuator and powering off a control surface position sensor;
step 8: judging whether the technical indexes tested in the steps 5 and 6 meet the design requirements, if not, closing a hydraulic oil source system, an aircraft movable airfoil surface adjustment detection system and an deflection angle detection system, reassembling and adjusting the airfoil surface or the actuator, repeating the steps 3, 4, 5, 6, 7 and 8 after adjustment until the technical indexes tested in the steps 5 and 6 meet the design requirements, and if the technical indexes tested in the steps 5 and 6 meet the design requirements, carrying out the test in the step 9;
step 9: and (3) selecting whether to continue testing other actuators of the movable airfoil surface to be detected, if so, repeating the steps 4, 5, 6, 7 and 8, otherwise, closing the hydraulic oil source system, the aircraft movable airfoil surface adjustment detection system and the deflection angle detection system, and ending the detection.
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| CN111017195B (en) * | 2019-12-24 | 2023-01-13 | 中国航空工业集团公司西安飞机设计研究所 | System and method for verifying non-command motion protection of slat |
| CN113335551A (en) * | 2020-03-02 | 2021-09-03 | 中航西飞民用飞机有限责任公司 | Zero setting method for electro-hydraulic servo actuator of airplane control surface |
| CN112783214A (en) * | 2021-01-15 | 2021-05-11 | 西安京东天鸿科技有限公司 | Unmanned aerial vehicle control system and method |
| CN113968358A (en) * | 2021-10-28 | 2022-01-25 | 西安羚控电子科技有限公司 | Operation inspection method and system of fixed-wing unmanned aerial vehicle |
| CN114194379B (en) * | 2021-11-22 | 2023-10-13 | 北京机电工程研究所 | Combined rudder method for improving control capacity of X-type pneumatic layout |
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