CN103969035A - Flap twist test system - Google Patents
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Abstract
本发明属于飞行控制系统监控技术领域，涉及一种襟翼扭曲测试系统。本发明利用LVDT传感器信号变化的可逆向性原理，在对每块舵面扭曲的测试时，将每块舵面两台滚珠丝杠上的LVDT进行串联后连接到控制器，即：将每两台滚珠丝杠所对应的LVDT间副边相互连接，原边连接到到控制器，此方法极大减少了扭曲传感器LVDT到控制器的接口数目，因此简化了控制器硬件电路的设计、降低了控制器复杂度、减小了控制器体积、重量以及可靠性，同时也减少了机上电缆数量。
The invention belongs to the technical field of flight control system monitoring, and relates to a flap twist testing system. The present invention utilizes the principle of reversibility of LVDT sensor signal changes, and when testing the distortion of each rudder surface, the LVDTs on the two ball screws of each rudder surface are connected in series to the controller, that is, each two The secondary sides of the LVDTs corresponding to the ball screw are connected to each other, and the primary side is connected to the controller. This method greatly reduces the number of interfaces between the twist sensor LVDT and the controller, thus simplifying the design of the hardware circuit of the controller and reducing the The complexity of the controller reduces the volume, weight and reliability of the controller, and also reduces the number of cables on the machine.
Description
技术领域technical field
本发明属于飞行控制系统监控技术领域，涉及一种襟翼扭曲测试系统。The invention belongs to the technical field of flight control system monitoring, and relates to a flap twist testing system.
背景技术Background technique
运输类飞机多采用襟翼和缝翼作为起飞时增升以及着陆时增升增阻功能，且一般来说这些襟翼及缝翼的驱动动力源均位于机身部分，其驱动动力均通过安装于机翼前后缘的扭力管传递到缝翼或襟翼，这些扭力管承受较大载荷，如果遇到舵面驱动某部分卡阻时控制系统仍旧控制输出，必将导致扭力管的断裂；或因老化、腐蚀、长期使用磨损等因素加上较大的扭转力矩而引起扭力管中间断裂。由于襟翼和缝翼的使用均在起飞及着陆危险性较大阶段，扭力管的断裂时而未加保护导致机翼结构的变化，甚至襟缝翼的较大扭曲均会导致飞机气动特性的变化及横向气动特性的不对称，从而造成造难性事故。Transport aircraft mostly use flaps and slats as the function of increasing lift during take-off and increasing lift and increasing resistance during landing, and generally speaking, the driving power sources of these flaps and slats are located in the The torsion tubes at the front and rear edges of the wing are transmitted to the slats or flaps, and these torsion tubes bear a large load. If the control system still controls the output when a certain part of the rudder drive is blocked, the torsion tube will inevitably break; or Due to factors such as aging, corrosion, long-term wear and tear plus a large torsional moment, the middle of the torque tube is broken. Since the use of flaps and slats is in the dangerous stages of take-off and landing, the breakage of the torsion tube without protection will lead to changes in the wing structure, and even a large twist of the flaps and slats will lead to changes in the aerodynamic characteristics of the aircraft And the asymmetry of lateral aerodynamic characteristics, thus causing difficult accidents.
通常，扭力管的断裂必然伴随着先期的舵面的扭曲，因此对运输类飞机对襟翼及缝翼的扭曲监测及保护便成为当代运输类飞机襟缝翼控制系统设计必不可少的部分之一。常规设计对飞机左右各具有2块襟翼舵面，每块舵面上具有两台滚珠丝杠，襟翼通过扭矩传输线系的襟翼舵面扭曲测试系统见图1所示，系统包括：左控制器1、左控制器2、左一滚珠丝杠3、左二滚珠丝杠4、左三滚珠丝杠5、左四滚珠丝杠6、右四滚珠丝杠7、右三滚珠丝杠8、右二滚珠丝杠9、右一滚珠丝杠10、左一襟翼扭曲传感器11、左二襟翼扭曲传感器12、左三襟翼扭曲传感器13、左四襟翼扭曲传感器14、右四襟翼扭曲传感器15、右三襟翼扭曲传感器16、右二襟翼扭曲传感器17、右一襟翼扭曲传感器18、左一襟翼19、左二襟翼20、右二襟翼21以及右一襟翼22，每台襟翼扭曲传感器为2电气两余度，分为通道A及通道B，左一襟翼扭曲传感器11、左二襟翼扭曲传感器12、左三襟翼扭曲传感器13、左四襟翼扭曲传感器14、右四襟翼扭曲传感器15、右三襟翼扭曲传感器16、右二襟翼扭曲传感器17及右一襟翼扭曲传感器18通道A连接到左控制器1，通道B连接到右控制器2，为左控制器1及右控制器2提供每台滚珠丝杠上的运动位置信息，左控制器1及右控制器2接收到这些信息后比较每片舵面上两台滚珠丝杠的位置信息，并判断一致性，当不一致超过事先给定的门限值时，输出襟翼扭曲信息，停止控制器对襟翼的收放控制，并对传输线系进行保护，防止故障蔓延，图2给出了常规设计方法对左一襟翼19检测时左一襟翼扭曲传感器11、左二襟翼扭曲传感器12与左控制器1及右控制器2的连接示意，图3给出了其具体接线关系，从图3可以分析出此系统所有具有双余度的8台襟翼扭曲传感器所需要左控制器1及右控制器2硬件接口数共96个。Usually, the fracture of the torque tube is bound to be accompanied by the distortion of the rudder surface in the early stage. Therefore, the monitoring and protection of the distortion of the flaps and slats of the transport aircraft has become one of the indispensable parts of the design of the flap and slat control system of the contemporary transport aircraft. . The conventional design has two flap rudder surfaces on the left and right sides of the aircraft, and each rudder surface has two ball screws. The flap rudder surface twist test system through the torque transmission line system is shown in Figure 1. The system includes: left Controller 1, Left Controller 2, Left 1 Ball Screw 3, Left 2 Ball Screw 4, Left 3 Ball Screw 5, Left 4 Ball Screw 6, Right 4 Ball Screw 7, Right 3 Ball Screw 8 , the second right ball screw 9, the first right ball screw 10, the first left flap distortion sensor 11, the second left flap distortion sensor 12, the third left flap distortion sensor 13, the fourth left flap distortion sensor 14, the fourth right flap Wing twist sensor 15, right third flap twist sensor 16, right second flap twist sensor 17, right first flap twist sensor 18, left first flap 19, left second flap 20, right second flap 21 and right first flap Wing 22, each flap twist sensor has 2 electrical redundancy, divided into channel A and channel B, the first left flap twist sensor 11, the second left flap twist sensor 12, the third left flap twist sensor 13, and the fourth left flap twist sensor Flap twist sensor 14, right 4th flap twist sensor 15, right 3rd flap twist sensor 16, right 2nd flap twist sensor 17 and right 1st flap twist sensor 18 Channel A is connected to left controller 1, channel B is connected to The right controller 2 provides the movement position information on each ball screw for the left controller 1 and the right controller 2. After receiving the information, the left controller 1 and the right controller 2 compare the two ball screws on each rudder surface. The position information of the lead screw, and judge the consistency. When the inconsistency exceeds the threshold value given in advance, the flap distortion information will be output, the controller will stop the flap retraction control, and the transmission line will be protected to prevent the fault from spreading. Fig. 2 has provided conventional design method to the left one flap twist sensor 11, left two flap twist sensors 12 and the connection schematic diagram of left controller 1 and right controller 2 when detecting left one flap 19, Fig. 3 has provided Its specific wiring relationship can be analyzed from Figure 3, and all 8 flap twist sensors with double redundancy in this system need a total of 96 hardware interfaces of the left controller 1 and the right controller 2.
从上可知，对于常规襟翼扭曲检测系统来说，襟翼扭曲传感器主要采用线性可变差动变压器，即LVDT（LinearVariable Differential Transformer）。由于具有余度配置的襟翼扭曲传感器的安装，极大地增加了襟翼控制系统控制器的接口数量，从而极大地增加了硬件电路，因此极大增加了控制器设计的难度、控制器工作电源消耗、重量、费用以及其自身的可靠性，同时也大大增加了系统电缆及电缆铺设工作量。It can be seen from the above that for the conventional flap twist detection system, the flap twist sensor mainly uses a linear variable differential transformer, namely LVDT (LinearVariable Differential Transformer). Due to the installation of the flap twist sensor with redundant configuration, the number of interfaces of the flap control system controller is greatly increased, thereby greatly increasing the hardware circuit, thus greatly increasing the difficulty of controller design and the operating power of the controller. Consumption, weight, cost, and its own reliability also greatly increase the workload of system cables and cable laying.
发明内容Contents of the invention
本发明要解决的技术问题是：为常规布局运输飞机襟翼系统，即：左右各2块襟翼舵面，每块襟翼舵面上具有两台滚珠丝杠，各襟翼舵面均通过位于机翼中央的动力驱动装置驱动襟翼扭矩传输线系而控制襟翼运动，提供一种襟翼扭曲测试系统，解决常规设计所带来的接口复杂问题，简化襟翼控制系统控制器的设计，从而在提高系统可靠性、优化系统设计的同时节省成本。The technical problem to be solved in the present invention is: for the conventional layout transport aircraft flap system, that is: each 2 flap rudder surfaces on the left and right, each flap rudder surface has two ball screw screws, and each flap rudder surface is passed through The power drive device located in the center of the wing drives the flap torque transmission line to control the flap movement, provides a flap twist test system, solves the interface complex problem caused by conventional design, and simplifies the design of the flap control system controller. Thereby saving cost while improving system reliability and optimizing system design.
本发明的技术方案为：Technical scheme of the present invention is:
一种襟翼扭曲测试系统，包括：左控制器1、左控制器2、左一滚珠丝杠3、左二滚珠丝杠4、左三滚珠丝杠5、左四滚珠丝杠6、右四滚珠丝杠7、右三滚珠丝杠8、右二滚珠丝杠9、右一滚珠丝杠10、左一襟翼扭曲传感器11、左二襟翼扭曲传感器12、左三襟翼扭曲传感器13、左四襟翼扭曲传感器14、右四襟翼扭曲传感器15、右三襟翼扭曲传感器16、右二襟翼扭曲传感器17、右一襟翼扭曲传感器18、左一襟翼19、左二襟翼20、右二襟翼21以及右一襟翼22；所述的八台襟翼扭曲传感器都为通道A及通道B两电气两余度的线性可变差动变压器，其中，A flap twist testing system, comprising: left controller 1, left controller 2, left first ball screw 3, left second ball screw 4, left third ball screw 5, left fourth ball screw 6, right four Ball screw 7, right third ball screw 8, right second ball screw 9, right first ball screw 10, left first flap twist sensor 11, left second flap twist sensor 12, left third flap twist sensor 13, Left 4th flap distortion sensor 14, right 4th flap distortion sensor 15, right 3rd flap distortion sensor 16, right 2nd flap distortion sensor 17, right 1st flap distortion sensor 18, left 1st flap 19, left 2nd flap 20. The second right flap 21 and the first right flap 22; the eight flap twist sensors are all linear variable differential transformers with two electrical redundancy in channel A and channel B, wherein,
左一襟翼扭曲传感器11通道A的原边连接到左控制器1，副边与左二襟翼扭曲传感器12通道A的副边并联后，左二襟翼扭曲传感器12通道A的原边连接到控制器1，The primary side of channel A of the first left flap twist sensor 11 is connected to the left controller 1, and after the secondary side is connected in parallel with the secondary side of channel A of channel 12 of the second left flap twist sensor, the primary side of channel A of the second left flap twist sensor 12 is connected to controller 1,
左三襟翼扭曲传感器13通道A的原边连接到左控制器1，副边与左四襟翼扭曲传感器14通道A的副边并联后，左四襟翼扭曲传感器14通道A的原边连接到控制器1，The primary side of the left three-flap twist sensor 13 channel A is connected to the left controller 1, and after the secondary side is connected in parallel with the secondary side of the left four-flap twist sensor 14 channel A, the primary side of the left four-flap twist sensor 14 channel A is connected to controller 1,
右四襟翼扭曲传感器15通道A的原边连接到左控制器1，副边与右三襟翼扭曲传感器16通道A的副边并联后，右三襟翼扭曲传感器16通道A的原边连接到控制器1，The primary side of the right four-flap twist sensor 15 channel A is connected to the left controller 1, and the secondary side is connected in parallel with the secondary side of the right three-flap twist sensor 16 channel A, and the primary side of the right three-flap twist sensor 16 channel A is connected to controller 1,
右二襟翼扭曲传感器17通道A的原边连接到左控制器1，副边与右一襟翼扭曲传感器18的通道A副边并联后，右一襟翼扭曲传感器18通道A的原边连接到控制器1，The primary side of channel A of the second right flap twist sensor 17 is connected to the left controller 1, and the secondary side is connected in parallel with the secondary side of channel A of the right flap twist sensor 18, and the primary side of channel A of the right flap twist sensor 18 is connected to controller 1,
左一襟翼扭曲传感器11通道B的原边连接到左控制器2，副边与左二襟翼扭曲传感器12通道B的副边并联后，左二襟翼扭曲传感器12通道B的原边连接到控制器2，The primary side of channel B of the first left flap twist sensor 11 is connected to the left controller 2, and the secondary side is connected in parallel with the secondary side of channel B of the second left flap twist sensor 12, and the primary side of channel B of the second left flap twist sensor 12 is connected to controller 2,
左三襟翼扭曲传感器13通道B的原边连接到左控制器2，副边与左四襟翼扭曲传感器14通道B的副边并联后，左四襟翼扭曲传感器14通道B的原边连接到控制器2，The primary side of the channel B of the left three-flap twist sensor 13 is connected to the left controller 2, and the secondary side is connected in parallel with the secondary side of the left four-flap twist sensor 14 channel B, and the primary side of the left four-flap twist sensor 14 channel B is connected to controller 2,
右四襟翼扭曲传感器15通道B的原边连接到左控制器2，副边与右三襟翼扭曲传感器16通道B的副边并联后，右三襟翼扭曲传感器16通道B的原边连接到控制器2，The primary side of the right four-flap twist sensor 15 channel B is connected to the left controller 2, and the secondary side is connected in parallel with the secondary side of the right three-flap twist sensor 16 channel B, and the primary side of the right three-flap twist sensor 16 channel B is connected to controller 2,
右二襟翼扭曲传感器17通道B的原边连接到左控制器2，副边与右一襟翼扭曲传感器18通道B的副边并联后，右一襟翼扭曲传感器18通道B的原边连接到控制器2。The primary side of channel B of the second right flap twist sensor 17 is connected to the left controller 2, and the secondary side is connected in parallel with the secondary side of channel B of the right flap twist sensor 18, and the primary side of channel B of the right flap twist sensor 18 is connected to controller 2.
本发明的有益效果为：利用LVDT传感器信号变化的可逆向性原理，在对每块舵面扭曲的测试时，将每块舵面两台滚珠丝杠上的LVDT进行串联后连接到控制器，即：将每两台滚珠丝杠所对应的LVDT间副边相互连接，原边连接到到控制器，此方法极大减少了扭曲传感器LVDT到控制器的接口数目，因此简化了控制器硬件电路的设计、降低了控制器复杂度、减小了控制器体积、重量以及可靠性，同时也减少了机上电缆数量。The beneficial effects of the present invention are: using the principle of reversibility of LVDT sensor signal change, when testing the distortion of each rudder surface, the LVDTs on the two ball screws of each rudder surface are connected in series to the controller, That is: connect the secondary sides of the LVDTs corresponding to every two ball screws to each other, and connect the primary side to the controller. This method greatly reduces the number of interfaces between the twist sensor LVDT and the controller, thus simplifying the hardware circuit of the controller. The design of the controller reduces the complexity of the controller, reduces the volume, weight and reliability of the controller, and also reduces the number of cables on the machine.
附图说明Description of drawings
图1为常规襟翼扭曲测试系统内部连接示意图；Figure 1 is a schematic diagram of the internal connections of a conventional flap twist test system;
图2为常规襟翼扭曲测试系统对左一襟翼19上左一襟翼扭曲传感器11及左二襟翼扭曲传感器12的连接示意图；Fig. 2 is the connection schematic diagram of conventional flap twist testing system to the left first flap twist sensor 11 and the left two flap twist sensors 12 on the left first flap 19;
图3为常规襟翼扭曲测试系统对左一襟翼19上左一襟翼扭曲传感器11及左二襟翼扭曲传感器12的接线图；Fig. 3 is the wiring diagram of the left first flap twist sensor 11 and the left second flap twist sensor 12 on the left first flap 19 by the conventional flap twist test system;
图4为本发明一种襟翼扭曲测试系统内部连接示意图；Fig. 4 is a schematic diagram of the internal connection of a flap twist testing system of the present invention;
图5为本发明一种襟翼扭曲测试系统中对左一襟翼19上左一襟翼扭曲传感器11及左二襟翼扭曲传感器12的连接示意图；Fig. 5 is a connection schematic diagram of the first left flap twist sensor 11 and the second left flap twist sensor 12 on the left first flap 19 in a flap twist test system of the present invention;
图6为本发明一种襟翼扭曲测试系统中对左一襟翼19上左一襟翼扭曲传感器11及左二襟翼扭曲传感器12的接线图；Fig. 6 is the wiring diagram of the left first flap twist sensor 11 and the left second flap twist sensor 12 on the left first flap 19 in a kind of flap twist test system of the present invention;
图7为将两LVDT串联后在与控制器连接情况下两LVDT位移同步的示意图；Fig. 7 is a schematic diagram of the displacement synchronization of two LVDTs connected to the controller after being connected in series;
图8为将两LVDT串联后在与控制器连接情况下两LVDT位移不同步的示意图。Fig. 8 is a schematic diagram of asynchronous displacement of two LVDTs connected to a controller after being connected in series.
具体实施方式Detailed ways
下面结合附图对本发明做进一步说明。The present invention will be further described below in conjunction with the accompanying drawings.
参加图4，一种襟翼扭曲测试系统，包括左控制器1、左控制器2、左一滚珠丝杠3、左二滚珠丝杠4、左三滚珠丝杠5、左四滚珠丝杠6、右四滚珠丝杠7、右三滚珠丝杠8、右二滚珠丝杠9、右一滚珠丝杠10、左一襟翼扭曲传感器11、左二襟翼扭曲传感器12、左三襟翼扭曲传感器13、左四襟翼扭曲传感器14、右四襟翼扭曲传感器15、右三襟翼扭曲传感器16、右二襟翼扭曲传感器17、右一襟翼扭曲传感器18、左一襟翼19、左二襟翼20、右二襟翼21以及右一襟翼22；所述的八台襟翼扭曲传感器都为通道A及通道B两电气两余度的线性可变差动变压器，其中，Refer to Figure 4, a flap twist test system, including left controller 1, left controller 2, left first ball screw 3, left second ball screw 4, left third ball screw 5, left fourth ball screw 6 , the fourth right ball screw 7, the third right ball screw 8, the second right ball screw 9, the first right ball screw 10, the first left flap twist sensor 11, the second left flap twist sensor 12, the third left flap twist Sensor 13, left 4th flap twist sensor 14, right 4th flap twist sensor 15, right 3rd flap twist sensor 16, right 2nd flap twist sensor 17, right 1st flap twist sensor 18, left 1st flap 19, left Two flaps 20, right two flaps 21 and right one flap 22; described eight flap twist sensors are all linear variable differential transformers with two electrical redundancy of channel A and channel B, wherein,
左一襟翼扭曲传感器11通道A的原边连接到左控制器1，副边与左二襟翼扭曲传感器12通道A的副边并联后，左二襟翼扭曲传感器12通道A的原边连接到控制器1，The primary side of channel A of the first left flap twist sensor 11 is connected to the left controller 1, and after the secondary side is connected in parallel with the secondary side of channel A of channel 12 of the second left flap twist sensor, the primary side of channel A of the second left flap twist sensor 12 is connected to controller 1,
左三襟翼扭曲传感器13通道A的原边连接到左控制器1，副边与左四襟翼扭曲传感器14通道A的副边并联后，左四襟翼扭曲传感器14通道A的原边连接到控制器1，The primary side of the left three-flap twist sensor 13 channel A is connected to the left controller 1, and after the secondary side is connected in parallel with the secondary side of the left four-flap twist sensor 14 channel A, the primary side of the left four-flap twist sensor 14 channel A is connected to controller 1,
右四襟翼扭曲传感器15通道A的原边连接到左控制器1，副边与右三襟翼扭曲传感器16通道A的副边并联后，右三襟翼扭曲传感器16通道A的原边连接到控制器1，The primary side of the right four-flap twist sensor 15 channel A is connected to the left controller 1, and the secondary side is connected in parallel with the secondary side of the right three-flap twist sensor 16 channel A, and the primary side of the right three-flap twist sensor 16 channel A is connected to controller 1,
右二襟翼扭曲传感器17通道A的原边连接到左控制器1，副边与右一襟翼扭曲传感器18的通道A副边并联后，右一襟翼扭曲传感器18通道A的原边连接到控制器1，The primary side of channel A of the second right flap twist sensor 17 is connected to the left controller 1, and the secondary side is connected in parallel with the secondary side of channel A of the right flap twist sensor 18, and the primary side of channel A of the right flap twist sensor 18 is connected to controller 1,
左一襟翼扭曲传感器11通道B的原边连接到左控制器2，副边与左二襟翼扭曲传感器12通道B的副边并联后，左二襟翼扭曲传感器12通道B的原边连接到控制器2，The primary side of channel B of the first left flap twist sensor 11 is connected to the left controller 2, and the secondary side is connected in parallel with the secondary side of channel B of the second left flap twist sensor 12, and the primary side of channel B of the second left flap twist sensor 12 is connected to controller 2,
左三襟翼扭曲传感器13通道B的原边连接到左控制器2，副边与左四襟翼扭曲传感器14通道B的副边并联后，左四襟翼扭曲传感器14通道B的原边连接到控制器2，The primary side of the channel B of the left three-flap twist sensor 13 is connected to the left controller 2, and the secondary side is connected in parallel with the secondary side of the left four-flap twist sensor 14 channel B, and the primary side of the left four-flap twist sensor 14 channel B is connected to controller 2,
右四襟翼扭曲传感器15通道B的原边连接到左控制器2，副边与右三襟翼扭曲传感器16通道B的副边并联后，右三襟翼扭曲传感器16通道B的原边连接到控制器2，The primary side of the right four-flap twist sensor 15 channel B is connected to the left controller 2, and the secondary side is connected in parallel with the secondary side of the right three-flap twist sensor 16 channel B, and the primary side of the right three-flap twist sensor 16 channel B is connected to controller 2,
右二襟翼扭曲传感器17通道B的原边连接到左控制器2，副边与右一襟翼扭曲传感器18通道B的副边并联后，右一襟翼扭曲传感器18通道B的原边连接到控制器2。The primary side of channel B of the second right flap twist sensor 17 is connected to the left controller 2, and the secondary side is connected in parallel with the secondary side of channel B of the right flap twist sensor 18, and the primary side of channel B of the right flap twist sensor 18 is connected to controller 2.
其连接示意图见图4所示，图5给出了本发明一种翼扭曲测试系统中对左一襟翼19上左一襟翼扭曲传感器11及左二襟翼扭曲传感器12的连接示意图，图6给出了本发明一种襟翼扭曲测试系统中对左一襟翼19上左一襟翼扭曲传感器11及左二襟翼扭曲传感器12的接线图，从图6可以分析出本发明一种襟翼扭曲测试系统中对所有具有双余度的8台襟翼扭曲传感器所需要左控制器1及右控制器2硬件接口数共32个。控制器对襟翼扭曲的检测原理见图7及图8所示，由于LVDT原理与变压器类似，基于其电感对称可逆性原理，当一块襟翼两滚珠丝杠同步也即未出现扭曲时，两LVDT同步运动，控制器将一定幅度的交流信号输送到A传感器原边后，在B传感器缘边端将接收到同样大小的信号，当一块襟翼两滚珠丝杠不同步也即出现扭曲时，两LVDT运动不同步，控制器将一定幅度的交流信号输送到A传感器原边后，在B传感器缘边端将接收到不同大小的信号，从而判断襟翼舵面的扭曲。Its connection schematic diagram is shown in Fig. 4, and Fig. 5 provides the connection schematic diagram of the left first flap twist sensor 11 and the left two flap twist sensors 12 on the left first flap 19 in a kind of wing twist test system of the present invention, Fig. 6 provides the wiring diagram of the left first flap twist sensor 11 and the left second flap twist sensor 12 on the left first flap 19 in a kind of flap twist test system of the present invention. From Fig. 6, it can be analyzed that a In the flap twist test system, a total of 32 hardware interfaces of left controller 1 and right controller 2 are required for all 8 flap twist sensors with double redundancy. The detection principle of the flap twist by the controller is shown in Figure 7 and Figure 8. Since the principle of the LVDT is similar to that of the transformer, based on the principle of inductance symmetry and reversibility, when the two ball screws of a flap are synchronized, that is, there is no distortion, the two LVDTs Synchronous movement, after the controller transmits an AC signal of a certain magnitude to the original side of the A sensor, a signal of the same size will be received at the edge of the B sensor. The LVDT movement is not synchronous. After the controller transmits the AC signal of a certain amplitude to the primary side of the A sensor, the edge of the B sensor will receive signals of different sizes, thereby judging the distortion of the flap rudder surface.
对于襟翼扭曲的检测主要是通过监控比较同一块襟翼上两滚珠丝杠的位置来实现，两滚珠丝杠的位置监控即可采用LVDT实现，同样也可在滚珠丝杠与传感器间加装位移与角度转换机构，即可采用旋转可变差动变压器，即RVDT（RotaryVariable DifferentialTransformer）实现，不管是采用LVDT还是RVDT，本发明所采用的串联式连接方法均适用。The detection of flap distortion is mainly realized by monitoring and comparing the positions of two ball screws on the same flap. The position monitoring of the two ball screws can be realized by LVDT, and it can also be installed between the ball screw and the sensor. The displacement and angle conversion mechanism can be realized by using a rotary variable differential transformer, that is, RVDT (Rotary Variable Differential Transformer). Regardless of whether LVDT or RVDT is used, the series connection method adopted in the present invention is applicable.
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