WO2021139837A2 - Wing swing amplitude testing device for airplane during dutch roll - Google Patents
Wing swing amplitude testing device for airplane during dutch roll Download PDFInfo
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- the wing swing amplitude device has a single function and cannot linearly simulate the Dutch roll operation of the aircraft with different strengths, making the test data more one-sided and unable to accurately obtain the optimal performance of the aircraft; in view of the above, we provide a method for wing swing when the aircraft is rolling in the Netherlands. Amplitude test device.
- the computer control system detects and analyzes the current in the voltage stabilization circuit in real time, and calculates the resistance value of the resistor connected to the voltage stabilization circuit by converting the measured current. According to the resistance of the resistors connected to the voltage stabilization loop, calculate the contact points of the resistors installed on the wing and the corresponding conductive pillar 8 to obtain the swing amplitude of the wing; the aircraft swing frequency is linearized by the speed control device Adjustment (that is, how fast the aircraft swings in a unit time, the faster you make an S-shaped maneuver per unit time, the more helpful it is to get rid of the rear dilemma and occupy a favorable position), which can linearly and continuously simulate the aircraft's rolling action in the Netherlands.
- the speed control device Adjustment that is, how fast the aircraft swings in a unit time, the faster you make an S-shaped maneuver per unit time, the more helpful it is to get rid of the rear dilemma and occupy a favorable position
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Abstract
The present invention relates to a wing swing amplitude testing device for an airplane during a Dutch roll. The wing swing amplitude testing device effectively solves the problem that an existing wing swing testing device cannot linearly and continuously simulate airplane maneuvering actions. According to the technical solution, the device can linearly simulate an airplane to execute Dutch roll actions of different strengths, and on the premise that safety is guaranteed, the limited action of the airplane is determined according to the swing amplitude of the wings, the device can further conduct corresponding adjustments according to different airplane types, and the wing swing amplitudes of different airplane models can be tested when the different airplane models execute a Dutch roll.
Description
本发明属于飞行测试技术领域，涉及一种用于飞机荷兰滚时机翼摇摆幅度测试装置。The invention belongs to the technical field of flight testing, and relates to a device for testing the swing amplitude of a wing when an airplane rolls in Holland.
荷兰滚类似简谐振动，规律性强，用于测试，目的在于用机动性争夺对方后面的有利位置，飞机就像钟摆一样，从上看就是蛇行路线（一边前进一边走S形路线），机动性好的获胜；飞机做该动作时，机翼承担较大负载（在快速前进且走S形路线过程中，机翼会产生上下摆动，此情况在翼尖处体现最明显），若做荷兰滚动作时过于激烈，会导致机翼受到不可逆损伤，飞机出厂时均会对其进行测试，确保安全的前提下，机翼能够承受的最大摆动幅度，现有用于测试飞机在做荷兰滚动作时机翼摇摆幅度的设备功能单一，不能线性模拟出飞机做不同强度的荷兰滚动作，使测试数据较为片面，无法精确获得飞机最优性能；鉴于以上，我们提供一种用于飞机荷兰滚时机翼摇摆幅度测试装置。The Dutch roll is similar to simple harmonic vibration with strong regularity. It is used for testing. The purpose is to use maneuverability to compete for a favorable position behind the opponent. The airplane is like a pendulum. From the top, it is a snaking route (while moving forward while taking an S-shaped route). Good performance wins; when the airplane does this action, the wing bears a larger load (the wing will swing up and down during the fast forward and S-shaped route, this situation is most obvious at the wing tip), if it is done in the Netherlands If the rolling operation is too intense, it will cause irreversible damage to the wing. The aircraft will be tested when it leaves the factory to ensure the maximum swing that the wing can withstand under the premise of safety. It is currently used to test the timing of the aircraft's rolling operation in the Netherlands. The wing swing amplitude device has a single function and cannot linearly simulate the Dutch roll operation of the aircraft with different strengths, making the test data more one-sided and unable to accurately obtain the optimal performance of the aircraft; in view of the above, we provide a method for wing swing when the aircraft is rolling in the Netherlands. Amplitude test device.
针对现有技术存在的不足，本发明可线性的模拟出飞机做不同强度的荷兰滚动作，确保安全前提下，根据机翼摇摆幅度确定飞机极限动作。In view of the shortcomings of the prior art, the present invention can linearly simulate the Dutch rolling action of the aircraft with different strengths, and under the premise of ensuring safety, the limit action of the aircraft can be determined according to the swing amplitude of the wing.
一种用于飞机荷兰滚时机翼摇摆幅度测试装置，包括检测架，其特征在于，检测架上转动安装有摆杆且摆杆上设有用于夹紧飞机的夹紧装置，摆杆上转动安装有L形架且L形架远离摆杆一端竖向滑动安装有安装板，两所述安装板上竖向转动安装有U形杆且U形杆两悬臂上分别可移动安装有检测板，两检测板相向一侧等距间隔设有若干可伸缩导电柱且机翼上下两端面分别设有电阻片，相配合的若干导电柱与电阻片串联于稳压回路中且位于U形杆同一悬臂上的若干导电柱之间并联，稳压回路中设有电流表且电流表电性连接有计算机控制系统；摆杆连接有设于检测架上的往复传动装置且往复传动装置经设于检测架上的调速装置驱动。A testing device for the swing amplitude of the wing of an airplane when it rolls in Holland, comprising a detection frame, which is characterized in that a swing rod is rotatably installed on the detection frame and a clamping device for clamping the aircraft is provided on the swing rod, and the swing rod is rotatably installed There is an L-shaped frame and one end of the L-shaped frame away from the pendulum rod is vertically slidably installed with a mounting plate. The two mounting plates are vertically rotatably mounted with a U-shaped rod. The two cantilever arms of the U-shaped rod are respectively movably installed with detection boards. A number of retractable conductive pillars are arranged at equal intervals on the opposite side of the detection board, and the upper and lower ends of the wing are respectively provided with resistors. The matched conductive pillars and resistors are connected in series in the voltage stabilizing loop and are located on the same cantilever of the U-shaped rod. A number of conductive columns are connected in parallel, an ammeter is provided in the voltage stabilizing loop, and the ammeter is electrically connected to a computer control system; the pendulum rod is connected with a reciprocating transmission device provided on the detection frame, and the reciprocating transmission device is adjusted on the detection frame Speed device drive.
本方案可较为线性的模拟出飞机做不同强度的荷兰滚动作，在确保飞行安全的前提下，根据机翼的摇摆幅度来确定飞机的极限动作。This solution can more linearly simulate the Dutch rolling action of the aircraft with different strengths. Under the premise of ensuring flight safety, the limit action of the aircraft can be determined according to the swing amplitude of the wings.
图1为本发明整体结构示意图。Figure 1 is a schematic diagram of the overall structure of the present invention.
图2为本发明飞机向一侧偏移时示意图。Figure 2 is a schematic diagram of the aircraft of the present invention when it deflects to one side.
图3为本发明飞机向另一侧偏移时示意图。Figure 3 is a schematic diagram of the aircraft of the present invention when it shifts to the other side.
图4为本发明调速装置结构示意图。Figure 4 is a schematic diagram of the structure of the speed regulating device of the present invention.
图5为本发明检测板与机翼配合关系示意图。Figure 5 is a schematic diagram of the matching relationship between the detection board and the wing of the present invention.
图6为本发明抵接杆、半圆环、飞机配合关系示意图。Fig. 6 is a schematic diagram of the matching relationship between the abutment rod, the semicircular ring, and the aircraft of the present invention.
图7为本发明锁定轮与锁定杆配合关系示意图。Fig. 7 is a schematic diagram of the matching relationship between the locking wheel and the locking rod of the present invention.
图8为本发明稳压回路连接示意图。Figure 8 is a schematic diagram of the connection of the voltage stabilizing loop of the present invention.
图9为本发明导电柱具体结构示意图。Fig. 9 is a schematic diagram of the specific structure of the conductive pillar of the present invention.
下面参考附图1至图9对实施例的详细说明，将可清楚的呈现。The following detailed description of the embodiments with reference to FIGS. 1 to 9 will be clearly presented.
实施例1，如图1所示，该装置在具体使用时，测试人员首先将待测试模型通过夹紧装置固定在摆杆2上并且调整好飞机的位置，随后通过转动安装在摆杆2上的L形架3，调整好安装板4相对于机翼位置（即，使得安装板4与机翼延伸方向一致，不同机型其机翼的翼展角度及方向都会有差异），随后通过竖向移动安装板4进而实现带动与之转动安装的U形杆5调整到与机翼相配合位置，即，使得机翼处于U形杆5两悬臂之间，如图2中所示，随后通过转动U形杆5将其与机翼调整为互相平行状态，如图2所示（机翼的设置往往与水平面产生一定夹角，需要转动U形杆5且调整其相对于水平面的角度以实现和机翼平行），实验人员在机翼上下两端面安装有电阻片（电阻片沿机翼延伸方向布置且图中未示出），随后将该装置置于风洞中且风洞中产生气流，模拟飞行状态，随后通过控制设于检测架1上的调速装置以一定速度运转且通过与之连接的往复传动装置实现带动摆杆2以一定频率做往复摇摆动作，模拟飞机在空中做荷兰滚时的真实动作，飞机一边前进一边做S形机动；我们将等距间隔安装在同一检测板6上的导电柱8相互并联，然后将与之配合的电阻片与若干并联的导电柱8进行串联后一起连入稳压回路，如图8所示，将若干导电柱8与稳压回路电源正极连接并且将电阻片靠近机身一端与稳压回路电源负极连接，稳压回路中串联有保护电阻和电流表，当飞机在高速气流下做往复摇摆动作时，远离机身的机翼摇摆幅度最大，随着机身摇摆频率不断加大，远离机身位置的导电柱8和电阻片靠近翼尖一端最先接触，使稳压回路接通且产生电流，计算机控制系统对稳压回路中的电流进行实时检测、分析，通过测得电流大小换算出电阻片连入稳压回路中阻值大小，根据电阻片连入稳压回路中阻值的大小，计算安装在机翼上的电阻片与相应导电柱8的接触点，得出机翼摇摆幅度；通过调速装置来对飞机摇摆频率进行线性调节（即，飞机在单位时间内摇摆的快慢，单位时间内做S形机动越快，则越有助于摆脱后方困境且占据有利位置），能够线性、连续的模拟出飞机在做荷兰滚动作时的不同状态，随着飞机往复摇摆频率加大，则机翼摇摆幅度也增大，此时越来越靠近机身位置的电阻片开始与检测板6上相应的导电柱8接触（此时靠近翼尖部位机翼将相应导电柱8压缩，为翼尖形变预留空间，电阻片靠近机身一端与稳压回路负极连接，电流会从最靠近机身位置的导电柱8经电阻片留回稳压回路负极，靠近翼尖位置的导电柱8虽与电阻片接触，但是被短路）；机翼上下两端面安装有电阻片且分别和与之对应检测板6上的若干导电柱8相配合，可实现对机翼上下摇摆幅度测试。Example 1, as shown in Figure 1, when the device is used in specific use, the tester first fixes the model to be tested on the swing rod 2 through the clamping device and adjusts the position of the aircraft, and then installs it on the swing rod 2 by rotating Adjust the position of the mounting plate 4 relative to the wing (that is, make the mounting plate 4 consistent with the extension direction of the wing, and the wingspan angle and direction of the wings of different models will be different), and then pass the vertical To move the mounting plate 4 to realize the adjustment of the U-shaped rod 5 that is rotatably installed with it to a position that matches the wing, that is, the wing is placed between the two cantilevers of the U-shaped rod 5, as shown in Figure 2, and then passed Turn the U-shaped rod 5 to adjust it and the wing to be parallel to each other, as shown in Figure 2 (the setting of the wing often produces a certain angle with the horizontal plane. It is necessary to rotate the U-shaped rod 5 and adjust its angle relative to the horizontal plane to achieve Parallel to the wing), the experimenters installed resistors on the upper and lower ends of the wing (the resistors are arranged along the extension direction of the wing and are not shown in the figure), and then the device is placed in the wind tunnel and airflow is generated in the wind tunnel , Simulate the flight state, and then control the speed regulating device installed on the detection frame 1 to run at a certain speed and through the reciprocating transmission device connected to it to drive the pendulum rod 2 to make reciprocating swing motions at a certain frequency, simulating the airplane in the air as the Netherlands The real action when rolling, the airplane moves forward while making an S-shaped maneuver; we connect the conductive posts 8 installed on the same detection board 6 at equal intervals in parallel with each other, and then connect the matched resistors with a number of parallel conductive posts 8 After connecting in series, connect them to the voltage stabilizing circuit. As shown in Figure 8, connect a number of conductive posts 8 to the positive pole of the voltage stabilizing circuit power supply, and connect the resistor piece close to the fuselage to the negative pole of the stabilizing circuit power supply. The voltage stabilizing circuit is connected in series with protection Resistor and ammeter. When the aircraft is swinging back and forth under high-speed airflow, the wing far away from the fuselage swings the most. As the swing frequency of the fuselage continues to increase, the conductive pillar 8 and the resistors far away from the fuselage are closer to the wing tip. One end is the first to contact, so that the voltage stabilization circuit is connected and the current is generated. The computer control system detects and analyzes the current in the voltage stabilization circuit in real time, and calculates the resistance value of the resistor connected to the voltage stabilization circuit by converting the measured current. According to the resistance of the resistors connected to the voltage stabilization loop, calculate the contact points of the resistors installed on the wing and the corresponding conductive pillar 8 to obtain the swing amplitude of the wing; the aircraft swing frequency is linearized by the speed control device Adjustment (that is, how fast the aircraft swings in a unit time, the faster you make an S-shaped maneuver per unit time, the more helpful it is to get rid of the rear dilemma and occupy a favorable position), which can linearly and continuously simulate the aircraft's rolling action in the Netherlands. At different states, as the reciprocating swing frequency of the aircraft increases, the swing amplitude of the wing also increases. At this time, the resistors that are getting closer to the fuselage begin to contact the corresponding conductive posts 8 on the detection board 6 (this time The wing near the wing tip compresses the corresponding conductive pillar 8 to reserve space for wing tip deformation. One end of the resistor near the fuselage is connected to the negative pole of the voltage regulator circuit, and the current will flow from the conductive pillar 8 closest to the fuselage through the resistor. The negative pole of the voltage regulator loop, although the conductive post 8 near the wing tip is in contact with the resistor, It is short-circuited); the upper and lower ends of the wing are equipped with resistors and are matched with a number of conductive posts 8 on the corresponding detection board 6 to realize the test of the swing amplitude of the wing.
实施例2，在实施例1的基础上，调速装置启动时带动半齿轮14转动，半齿轮14转动则带动齿框15做横向往复移动，齿框15上端面设有与往复齿轮16啮合的齿系进而带动往复齿轮16做往复转动，实现带动摆杆2做往复摇摆动作。Embodiment 2, on the basis of embodiment 1, when the speed regulating device is activated, the half gear 14 is driven to rotate, and the rotation of the half gear 14 drives the gear frame 15 to move laterally. The upper end surface of the gear frame 15 is provided with a gear that meshes with the reciprocating gear 16 The tooth system then drives the reciprocating gear 16 to reciprocate, so as to drive the pendulum rod 2 to reciprocate.
实施例3，在实施例2基础上，摇摆电机24与调节电机22经计算机控制系统控制，当摇摆电机24启动时带动与之连接的第一锥形盘17转动，第一锥形盘通过钢带实现带动另一组相配合的第一锥形盘、第二锥形盘转动，并且另一组中第一锥形盘经带轮组驱动半齿轮14转动，带动摆杆2往复摇摆；随着实验进行，计算机控制系统控制调节电机22启动且转动一定角度，带动两调节齿轮21进行转动，两调节齿轮21转动则带动两调节丝杠20转动，我们设定两调节丝杠20转动时能够分别带动与之螺纹配合安装的圆板19沿同向在检测架1上进行纵向移动，两第一锥形盘17以及两第二锥形盘18分别呈对角设置，此时与摇摆电机24直接连接的第一锥形盘、第二锥形盘为输入盘，与半齿轮14连接的第一锥形盘、第二锥形盘为输出盘，随着两第一锥形盘的移动，使得钢带与两组锥型盘的传动半径发生变化，实现改变输出盘转动速度，实现对半齿轮14转速的线性、连续的调节，通过相两组锥型盘可模拟出飞机以不同强度下做S形机动时的动作（即，S形曲线中相邻两弧形曲线之间的距离越大则S形机动越慢，反之则越大）；计算机控制系统每隔相应时间控制调节电机22启动且转动相应角度，来调整摆杆2的往复摇摆频率，能够线性、连续测得飞机以不同强度做荷兰滚动作时机翼摇摆幅度且最终寻找飞机所能做的最大强度的荷兰滚动作。In Embodiment 3, on the basis of Embodiment 2, the swing motor 24 and the adjustment motor 22 are controlled by a computer control system. When the swing motor 24 is started, the first conical disc 17 connected to it is driven to rotate. The belt realizes to drive another group of matched first and second conical discs to rotate, and the first conical disc in the other group drives the half gear 14 to rotate through the pulley group, driving the swing lever 2 to reciprocate; As the experiment progresses, the computer control system controls the adjustment motor 22 to start and rotate a certain angle to drive the two adjustment gears 21 to rotate. The rotation of the two adjustment gears 21 drives the two adjustment screws 20 to rotate. We set the two adjustment screws 20 to rotate. The circular plate 19 fitted with the screw thread is driven to move longitudinally on the detection frame 1 in the same direction. The two first conical discs 17 and the two second conical discs 18 are arranged diagonally, at this time, and the swing motor 24 The first conical disc and the second conical disc directly connected are the input discs, and the first conical disc and the second conical disc connected to the half gear 14 are the output discs. As the two first conical discs move, The transmission radius of the steel belt and the two sets of cone-shaped discs is changed, the rotation speed of the output disc is changed, and the linear and continuous adjustment of the rotation speed of the half gear 14 is realized. The two sets of cone-shaped discs can simulate the aircraft under different strengths. The action when doing an S-shaped maneuver (ie, the larger the distance between two adjacent arc-shaped curves in the S-shaped curve, the slower the S-shaped maneuver, and vice versa); the computer control system controls and adjusts the motor 22 every corresponding time Start and rotate the corresponding angle to adjust the reciprocating swing frequency of the pendulum rod 2, which can linearly and continuously measure the swing amplitude of the wing when the aircraft performs Dutch rolling operations with different strengths, and finally find the highest intensity Dutch rolling operations that the aircraft can do.
实施例4，在实施例1的基础上，如图9，当机翼未触碰到导电板28时，处于机翼上方的导电板28（导电板面向机翼一侧安装有导电片且其余部分由较轻材料制成，导电板28受到的离心力可忽略）在伸缩弹簧29、抵触杆32和设于滑筒27内的若干抵接齿31配合作用下处于限位状态，我们在处于机翼下方的滑筒内且与导电板滑动安装部位设有摩擦阻尼材质，在伸缩弹簧29与摩擦阻尼材质作用下使处于机翼下方的导电板处于限位状态；导电板28与滑动接触部位以及滑筒27为绝缘材质，当机翼触碰到导电板28时，方才在挤压力的情况下向滑筒27内移动（在导电板28向滑筒27内移动时，迫使两抵触杆32朝着压缩复位弹簧30的方向转动，以至越过相邻的一个抵接齿31后，在复位弹簧30作用下完成复位且抵触在相应抵接齿31上，实现对导电板28定位），随着实验强度加大，机翼摇摆的幅度也增大，越靠近机身位置的导电板28与安装在机翼上的电阻片靠近机身位置接触，通过测得稳压回路中的电流，计算机翼形变量；完成实验后需将导电板28进行复位，我们在导电板28上端位置安装有电磁铁且两抵触杆32面向电磁铁一侧设有铁片，当需要复位时，只需将电磁铁通电将两抵触杆32朝着压缩复位弹簧30的方向移动（抵触杆不再抵触于抵接齿），即可将导电板28移动至初始位置，随后控制电磁铁失电即可，可将安装在同一检测板6上的若干导电板28内的电磁铁共同串联并且由同一电源供电，同步完成复位动作。Example 4, on the basis of Example 1, as shown in Figure 9, when the wing does not touch the conductive plate 28, the conductive plate 28 above the wing (the conductive plate faces the side of the wing is installed with a conductive sheet and the rest Part of it is made of lighter materials, and the centrifugal force on the conductive plate 28 is negligible.) Under the cooperative action of the telescopic spring 29, the abutment rod 32, and a number of abutment teeth 31 provided in the sliding cylinder 27, it is in a limited position. A friction damping material is provided in the sliding cylinder under the wing and the sliding installation part with the conductive plate. Under the action of the telescopic spring 29 and the friction damping material, the conductive plate under the wing is in a limit state; the conductive plate 28 and the sliding contact part and The sliding cylinder 27 is made of insulating material. When the wing touches the conductive plate 28, it moves into the sliding cylinder 27 under the condition of squeezing force (when the conductive plate 28 moves into the sliding cylinder 27, the two contact rods 32 are forced Rotate in the direction of compressing the return spring 30, so that after passing over an adjacent abutting tooth 31, the resetting is completed under the action of the return spring 30 and abutting on the corresponding abutting tooth 31, realizing the positioning of the conductive plate 28), with The intensity of the experiment increases, and the swing amplitude of the wing also increases. The conductive plate 28 closer to the fuselage is in contact with the resistors installed on the wing near the fuselage. By measuring the current in the voltage stabilization loop, the computer wing Deformation amount; after the experiment is completed, the conductive plate 28 needs to be reset. We install an electromagnet at the upper end of the conductive plate 28 and the two interference rods 32 are equipped with iron plates on the side facing the electromagnet. When resetting is required, only the electromagnet is required Move the two resisting rods 32 toward the direction of the compression return spring 30 (the resisting rods no longer interfere with the abutting teeth), then the conductive plate 28 can be moved to the initial position, and then the electromagnet can be controlled to de-energize, and the installation can be The electromagnets in the several conductive plates 28 on the same detection board 6 are connected in series and powered by the same power source to complete the reset operation synchronously.
如图6，摆杆2上螺纹配合有转动螺杆23且转动螺杆23与L形架3之间轴向滑动安装，当旋转转动螺杆23时即可带动L形架3转动，调整L形架3相对于机翼位置，如图7，L形架3上转动安装有与安装板4螺纹配合的升降丝杠33，通过转动升降丝杠33调节安装板4，转动螺杆23、升降丝杠33以及双向丝杠12均设有自锁螺纹，在U形杆5与安装板4转动部位轴向滑动有锁定轮26且锁定轮26与U形杆5转轴之间连接有收缩弹簧（图中未示出），安装板4上设有锁定杆25且锁定轮26上设有若干锁定孔，需要转动U形杆5时，向外拉动锁定轮26使其解锁，即可转动且调节U形杆5的角度，松开锁定轮26，锁定杆25再次插入至相应锁定孔中，对U形杆5锁定，将检测板6与U形杆5悬臂之间经电动推杆7连接，可实现调整检测板6距离机翼表面的距离；如图6，夹紧装置包括与摆杆连接的半圆环10且半圆环上下两端竖向滑动有抵接杆11（两抵接杆11之间配合有双向丝杠12），将飞机模型放置在半圆环10内且通过转动双向丝杠12实现带动两抵接杆11进行相向移动，将机身夹紧定位。As shown in Figure 6, the screw thread on the pendulum rod 2 is fitted with a rotating screw 23 and the rotating screw 23 is axially slidably installed between the rotating screw 23 and the L-shaped frame 3. When the rotating screw 23 is rotated, the L-shaped frame 3 can be driven to rotate, and the L-shaped frame 3 can be adjusted. Relative to the position of the wing, as shown in Figure 7, the L-shaped frame 3 is rotatably installed with a lifting screw 33 threaded with the mounting plate 4. The mounting plate 4 is adjusted by rotating the lifting screw 33, the screw 23, the lifting screw 33 and The two-way screw 12 is provided with self-locking threads. A locking wheel 26 is axially slid at the rotating part of the U-shaped rod 5 and the mounting plate 4, and a contraction spring is connected between the locking wheel 26 and the rotating shaft of the U-shaped rod 5 (not shown in the figure). Out), the mounting plate 4 is provided with a locking lever 25 and the locking wheel 26 is provided with a number of locking holes. When the U-shaped lever 5 needs to be rotated, pull the locking wheel 26 outward to unlock it, and then the U-shaped lever 5 can be rotated and adjusted The locking wheel 26 is loosened, the locking rod 25 is inserted into the corresponding locking hole again to lock the U-shaped rod 5, and the detection plate 6 and the U-shaped rod 5 cantilever are connected through the electric push rod 7, which can realize the adjustment detection The distance between the plate 6 and the surface of the wing; as shown in Fig. 6, the clamping device includes a semicircular ring 10 connected with the pendulum rod, and the upper and lower ends of the semicircular ring slide vertically with abutting rods 11 (the two abutting rods 11 cooperate with each other There is a two-way screw 12), the aircraft model is placed in the semicircular ring 10 and the two abutting rods 11 are driven to move toward each other by rotating the two-way screw 12, and the fuselage is clamped and positioned.
可较为线性的模拟出飞机做不同强度的荷兰滚动作，在确保飞行安全的前提下，根据机翼的摇摆幅度来确定飞机的极限动作，而且该装置可针对不同的机型进行相应的调整，针对不同机型均可实现对其做荷兰滚时的机翼摇摆幅度进行测试。It can be more linearly simulated that the aircraft does Dutch rolling operations of different strengths. Under the premise of ensuring flight safety, the limit action of the aircraft is determined according to the swing amplitude of the wings, and the device can be adjusted accordingly for different models. For different models, the wing swing amplitude of the Dutch roll can be tested.
Claims (4)
- 一种用于飞机荷兰滚时机翼摇摆幅度测试装置，包括检测架（1），其特征在于，所述检测架（1）上转动安装有摆杆（2）且摆杆（2）上设有用于夹紧飞机的夹紧装置，摆杆（2）上转动安装有L形架（3）且L形架（3）远离摆杆（2）一端竖向滑动安装有安装板（4），两安装板（4）上竖向转动安装有U形杆（5）且U形杆（5）两悬臂上分别可移动安装有检测板（6），两所述检测板（6）相向一侧等距间隔设有若干可伸缩的导电柱（8）且机翼上下两端面分别设有电阻片，相配合的若干导电柱（8）与电阻片串联于稳压回路中且位于U形杆（5）同一悬臂上的若干导电柱（8）之间并联，所述稳压回路中设有电流表且电流表电性连接有计算机控制系统；A testing device for the swing amplitude of the wing of an airplane during Dutch roll, comprising a detection frame (1), characterized in that a swing rod (2) is rotatably installed on the detection frame (1) and a swing rod (2) is provided with For the clamping device for clamping the aircraft, an L-shaped frame (3) is rotatably installed on the swing rod (2), and an end of the L-shaped frame (3) away from the swing rod (2) is vertically slid and installed with a mounting plate (4), two A U-shaped rod (5) is installed on the mounting plate (4) for vertical rotation, and the two cantilevers of the U-shaped rod (5) are respectively movably installed with a detection plate (6), and the two detection plates (6) are opposite to one side, etc. A number of retractable conductive posts (8) are arranged at intervals, and the upper and lower ends of the wing are respectively equipped with resistors. The matched conductive posts (8) and resistors are connected in series in the voltage stabilizing loop and are located on the U-shaped rod (5). ) A number of conductive columns (8) on the same cantilever are connected in parallel, an ammeter is provided in the voltage stabilizing loop, and the ammeter is electrically connected to a computer control system;所述摆杆（2）连接有设于检测架（1）上的往复传动装置且往复传动装置经设于检测架（1）上的调速装置驱动。The pendulum rod (2) is connected with a reciprocating transmission device provided on the detection frame (1), and the reciprocating transmission device is driven by a speed regulating device provided on the detection frame (1).
- 根据权利要求1所述的一种用于飞机荷兰滚时机翼摇摆幅度测试装置，其特征在于，往复传动装置包括横向滑动安装于检测架（1）的齿框（15）且齿框（15）啮合有转动安装于检测架（1）上的半齿轮（14），齿框（15）驱动有转动安装于检测架（1）上的往复齿轮（16）且往复齿轮（16）驱动摆杆（2）转动，半齿轮（14）经调速装置驱动。The device for testing the swing amplitude of the wing of an airplane during Dutch roll according to claim 1, characterized in that the reciprocating transmission device comprises a tooth frame (15) and a tooth frame (15) which are mounted on the detection frame (1) in a lateral sliding manner. The gear frame (15) drives the reciprocating gear (16) that is rotatably installed on the detection frame (1) and the reciprocating gear (16) drives the swing lever ( 2) When rotating, the half gear (14) is driven by the speed regulating device.
- 根据权利要求2所述的一种用于飞机荷兰滚时机翼摇摆幅度测试装置，其特征在于，调速装置包括设于检测架（1）上的两组锥盘且两组锥盘之间配合有钢带，每组锥盘包括第一锥形盘（17）、第二锥形盘（18），第一锥形盘（17）与检测架（1）转动安装，第二锥形盘（18）同轴心转动安装有圆板（19）且圆板（19）纵向滑动安装于检测架（1），两圆板（19）纵向间隔设置且两分别螺纹配合有转动安装于检测架（1）上的调节丝杠（20），两调节丝杠（20）纵向同侧套固有啮合的调节齿轮（21）且其中一个调节齿轮（21）经调节电机（22）驱动，其中一个第一锥形盘（17）经摇摆电机（24）驱动且另一所述第一锥形盘（17）驱动半齿轮（14）。A testing device for wing swing amplitude during Dutch roll of aircraft according to claim 2, characterized in that the speed regulating device comprises two sets of cone discs arranged on the detection frame (1) and the two sets of cone discs cooperate with each other. There are steel belts, each group of cone discs includes a first cone disc (17), a second cone disc (18), the first cone disc (17) and the detection frame (1) are rotatably installed, and the second cone disc ( 18) A circular plate (19) is installed coaxially with rotation and the circular plate (19) is slidably installed on the detection frame (1) longitudinally. The two circular plates (19) are longitudinally spaced apart and two separate threads are fitted to rotate and are installed on the detection frame ( 1) On the adjustment screw (20), the two adjustment screws (20) are longitudinally set on the same side with the inherently meshing adjustment gears (21) and one of the adjustment gears (21) is driven by the adjustment motor (22), one of which is the first The cone disc (17) is driven by the swing motor (24) and the other first cone disc (17) drives the half gear (14).
- 根据权利要求1所述的一种用于飞机荷兰滚时机翼摇摆幅度测试装置，其特征在于，导电柱（8）包括固定安装在U形杆（5）上的滑筒（27）且滑筒（27）内竖向滑动安装有导电板（28），导电板（28）与滑筒（27）之间连接有伸缩弹簧（29）且滑筒（27）内部轴向两侧设有抵接齿（31），导电板（28）上转动安装有两抵触杆（32）且两抵触杆（32）与导电板（28）之间连接有复位弹簧（30）。A testing device for wing swing amplitude during Dutch roll of an airplane according to claim 1, wherein the conductive column (8) comprises a sliding cylinder (27) fixedly mounted on the U-shaped rod (5) and the sliding cylinder (27) A conductive plate (28) is installed in the vertical sliding direction, a telescopic spring (29) is connected between the conductive plate (28) and the sliding cylinder (27), and the inner axial sides of the sliding cylinder (27) are provided with abutment The teeth (31) and the conductive plate (28) are rotatably mounted with two resisting rods (32), and a return spring (30) is connected between the two resisting rods (32) and the conductive plate (28).
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| CN114486154A (en) * | 2021-12-28 | 2022-05-13 | 中国航天空气动力技术研究院 | Two-degree-of-freedom wing panel supporting device and wind tunnel test equipment |
| CN115183857A (en) * | 2022-09-13 | 2022-10-14 | 山东迈易特传动有限公司 | Vibration intensity detection device for variable-frequency speed regulation all-in-one machine |
| CN117087869A (en) * | 2023-08-04 | 2023-11-21 | 中国人民解放军总参谋部第六十研究所 | Unmanned aerial vehicle test auxiliary device |
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| CN107512405B (en) * | 2017-08-01 | 2019-12-31 | 中国航空工业集团公司西安飞机设计研究所 | Vibration simulation test and data use method for light airplane |
| CN107869960B (en) * | 2017-11-22 | 2019-09-10 | 东南大学 | A kind of aircraft wing deformation measuring device, installation method and test method |
| GB201814241D0 (en) * | 2018-08-31 | 2018-10-17 | Airbus Operations Gmbh | Deformation sensing system |
| CN111169654A (en) * | 2019-12-25 | 2020-05-19 | 中国航空工业集团公司西安飞机设计研究所 | Deformation monitoring device of aircraft wing |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114486154A (en) * | 2021-12-28 | 2022-05-13 | 中国航天空气动力技术研究院 | Two-degree-of-freedom wing panel supporting device and wind tunnel test equipment |
| CN115183857A (en) * | 2022-09-13 | 2022-10-14 | 山东迈易特传动有限公司 | Vibration intensity detection device for variable-frequency speed regulation all-in-one machine |
| CN115183857B (en) * | 2022-09-13 | 2022-12-09 | 山东迈易特传动有限公司 | Vibration intensity detection device for variable-frequency speed regulation all-in-one machine |
| CN117087869A (en) * | 2023-08-04 | 2023-11-21 | 中国人民解放军总参谋部第六十研究所 | Unmanned aerial vehicle test auxiliary device |
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