An adaptive clamping device for detecting the clearance of aircraft main control surfaces

Abstract

This utility model relates to the field of aircraft control surface clearance detection technology, specifically to an adaptive clamping device for detecting the clearance of aircraft main control surfaces. It includes a clamping mechanism, a loading clamping mechanism, a movable surface clamping mechanism, a control box, and a control host. The clamping mechanism and the loading clamping mechanism are connected to form a ring structure. The movable surface clamping mechanism is located inside the ring structure, and its inner side is equipped with several lifting block assemblies and pressure sensors that conform to the stabilizer surface. The loading clamping mechanism is equipped with a displacement adjustment assembly for adjusting the height of the movable surface clamping mechanism. The movable surface clamping mechanism is U-shaped, and its inner side is equipped with control surface clamping assemblies that conform to the movable surface. Pressure sensors are located on the contact surfaces. The displacement adjustment assembly and each pressure sensor are connected to the control host via the control box. This utility model uses force loading to cause the movable surface to rotate, and obtains the free clearance between the movable surface and the stabilizer surface by measuring the rotation angle, thereby improving the accuracy and reliability of the clearance measurement results.

Description

Technical Field

[0001] This utility model relates to the field of aircraft control surface clearance detection technology, and more specifically, to an adaptive clamping device for detecting the clearance of aircraft main control surfaces. Background Technology

[0002] Aircraft control surface (aileron, elevator, rudder) clearance measurement is a core aspect of ensuring flight safety. Clearance measurement involves measuring the free travel of the relative deflection angle between the moving surfaces and the stabilizer. Control surface clearance directly affects the response accuracy of the flight control system. According to relevant standards, control surface clearance must be strictly controlled within the design tolerance range; otherwise, it may lead to aerodynamic performance degradation, control jamming, or even structural fatigue damage. Both factory inspections and periodic inspections during service require clearance measurement to verify the condition of the control surfaces in order to identify potential faults in advance.

[0003] In the process of measuring the clearance of aircraft control surfaces, the performance of the clamping device directly affects the detection accuracy and the safety of the control surface clearance. Chinese invention patent with publication number CN113443168A provides a device for fixing and detecting the clearance of aircraft control surfaces, and specifically discloses a pressure loading mechanism and an automatic testing system loaded with a test program. The control surface clamp in the pressure loading mechanism is a U-shaped structure, and a clamping disc is provided on the inner surface of the U-shaped structure. A handle is provided on the control surface clamp. This prior art can control the vertical displacement of the height adjustment rod through the adjustment disc to measure the control surfaces of different models of aircraft, and the aircraft control surfaces can be installed and fixed in the control surface clamp according to the actual height. However, this prior art still has the following defects: (1) The force loading platform is bulky and heavy, which is not convenient for on-site operation; (2) The force loading platform requires a complex support structure, has poor stability, and is easily affected by environmental vibration; (3) The clamping device is difficult to adapt to control surfaces with different curvatures; (4) The clamping force control accuracy is low, which can easily damage the control surfaces; (5) There is a lack of real-time force feedback, and safety is difficult to guarantee.

[0004] The aforementioned defects seriously affect the accuracy and safety of the inspection, and urgently need to be improved through technological innovation to meet the stringent requirements for accuracy and safety in aircraft control surface clearance inspection. Utility Model Content

[0005] The purpose of this invention is to provide an adaptive clamping device for detecting the clearance of the main control surfaces of an aircraft, so as to solve the technical problems pointed out in the background art.

[0006] This utility model is achieved through the following technical solution: an adaptive clamping device for detecting the clearance of the main control surfaces of an aircraft, suitable for measuring the clearance of the aileron moving surfaces and the elevator moving surfaces, including a clamping mechanism, a loading clamping mechanism and a moving surface clamping mechanism;

[0007] Both the clamping mechanism and the loading clamping mechanism are U-shaped, and their free ends are connected to form a ring structure. The movable surface clamping mechanism is located inside the ring structure.

[0008] The inner sides of the upper and lower rings of the annular structure are provided with several lifting block assemblies that fit into the stabilizing surface, and the fitting surface of the lifting block assembly is provided with a first pressure sensor.

[0009] The loading clamping mechanism is provided with a displacement adjustment component for adjusting the height position of the movable surface clamping mechanism, and the clamping mechanism and the loading clamping mechanism are respectively provided with locking components for adjusting and maintaining the clamping state between the lifting block assembly and the stable surface.

[0010] The movable surface clamping mechanism is a "U" shaped structure, and a rudder surface clamping assembly that fits into the movable surface is provided inside the "U" shaped structure. The fitting surface of the rudder surface clamping assembly is provided with a second pressure sensor.

[0011] It also includes a control box and a control host. The first pressure sensor, the displacement adjustment component and the second pressure sensor are all electrically connected to the control box, and the control box is electrically connected to the control host.

[0012] According to a preferred embodiment, both the clamping mechanism and the loading clamping mechanism include an upper inclined beam group, a lower inclined beam group, an upper crossbeam, and a lower crossbeam. The upper inclined beam group and the lower inclined beam group are each composed of two pairs of parallel inclined beams. The upper end of the upper inclined beam group is hinged to the first end of the upper crossbeam, the lower end of the upper inclined beam group is hinged to the upper end of the lower inclined beam group, and the lower end of the lower inclined beam group is hinged to the first end of the lower crossbeam. The angle between the upper inclined beam group and the lower inclined beam group is an acute angle.

[0013] According to a preferred embodiment, the locking component on the clamping mechanism includes a first handwheel, a first base plate, a drive disk, an upper connecting rod, and a lower connecting rod;

[0014] The first base plate is connected between the upper inclined beam group and the lower inclined beam group, and its upper and lower ends are respectively hinged to the upper inclined beam group and the lower inclined beam group.

[0015] The drive disc is disposed between parallel inclined beams. The drive disc is provided with a threaded groove. The first handwheel is threadedly engaged with the first base plate. The end of the first handwheel that passes through the first base plate is threadedly engaged with the threaded groove. The upper end of the drive disc is hinged to the first end of the upper connecting rod. The second end of the upper connecting rod is hinged to the upper crossbeam on the inner side of the upper inclined beam group. The lower end of the drive disc is hinged to the first end of the lower connecting rod. The second end of the lower connecting rod is hinged to the lower crossbeam on the inner side of the lower inclined beam group.

[0016] According to a preferred embodiment, the displacement adjustment assembly includes a servo motor housing, a first fixed pulley group, a first pull cable, a second fixed pulley group, and a second pull cable;

[0017] The servo motor box is connected between the upper inclined beam group and the lower inclined beam group, and its upper and lower ends are respectively hinged to the upper inclined beam group and the lower inclined beam group.

[0018] The servo motor housing contains a servo motor, a reducer, and a transmission mechanism. The output shaft of the servo motor is connected to the reducer, and the output shaft of the reducer is connected to the transmission mechanism. The transmission mechanism is used to realize the vertical change of the torque direction of the servo motor. The transmission mechanism has a first output shaft located on the first side of the servo motor housing and a second output shaft located on the second side of the servo motor housing. The first side of the servo motor housing is the opposite side of the second side of the servo motor housing.

[0019] The first fixed pulley group is arranged on the same side as the first output shaft of the transmission mechanism, and the second fixed pulley group is arranged on the same side as the second output shaft of the transmission mechanism. The first end of the first pull cable is connected to the first output shaft of the transmission mechanism, and the second end of the first pull cable is connected to the upper part of the movable surface clamping mechanism via the first fixed pulley group. The first end of the second pull cable is connected to the second output shaft of the transmission mechanism, and the second end of the second pull cable is connected to the lower part of the movable surface clamping mechanism via the second fixed pulley group.

[0020] According to a preferred embodiment, both the first pull wire and the second pull wire are equipped with tension sensors, and the tension sensors are electrically connected to the control box.

[0021] According to a preferred embodiment, both the first fixed pulley group and the second fixed pulley group consist of two fixed pulleys, which are respectively located at the upper and lower ends of the inclined beam inside the upper / lower inclined beam group, and the tension sensor is installed on the tension line between the two fixed pulleys.

[0022] According to a preferred embodiment, the locking component on the loading clamping mechanism is composed of a first locking component corresponding to the lower inclined beam group and a second locking component corresponding to the upper inclined beam group. Both the first locking component and the second locking component include a second handwheel and a second base plate.

[0023] The second base plate is connected between parallel inclined beams. The second handwheel is threadedly engaged with the second base plate. The end of the second handwheel that passes through the second base plate abuts against the pivot at the hinge of the upper / lower end of the servo motor box.

[0024] According to a preferred embodiment, the movable surface clamping mechanism includes a first "U"-shaped bracket, a second "U"-shaped bracket, and a crossbar assembly;

[0025] The crossbar assembly includes a first crossbar and a second crossbar. The first crossbar is connected between the first free ends of the first "U"-shaped bracket and the second "U"-shaped bracket, and the second crossbar is connected between the second free ends of the first "U"-shaped bracket and the second "U"-shaped bracket.

[0026] The first "U"-shaped bracket and the second "U"-shaped bracket each have a set of opposing rudder surface clamping assemblies on their inner sides. The rudder surface clamping assembly consists of a third handwheel, a third base plate and a second pressure sensor. The third base plate is connected to the free end of the "U"-shaped bracket. The third handwheel is threadedly engaged with the third base plate. The third handwheel extends through the end of the third base plate to the inner side of the "U"-shaped bracket and is connected to the second pressure sensor.

[0027] According to a preferred embodiment, one or more of the upper crossbeam, lower crossbeam, upper inclined beam assembly, lower inclined beam assembly, and "U"-shaped bracket are provided with sensor wiring interfaces.

[0028] This utility model also provides an adaptive clamping device for detecting the clearance of the main control surfaces of an aircraft, including the adaptive clamping device for detecting the clearance of the main control surfaces of an aircraft as described above, which is suitable for measuring the clearance of the rudder moving surfaces, and also includes a vertical tail pylon assembly.

[0029] The vertical tail pylon assembly includes a first pylon located on the first side of the rudder and a second pylon located on the second side of the rudder. The first end of the first pylon is hinged to the upper crossbeam of the loading clamping mechanism, and the first end of the second pylon is hinged to the lower crossbeam of the loading clamping mechanism. The second ends of the first pylon and the second pylon are connected to reserved interfaces on both sides of the rudder.

[0030] The technical solution of the adaptive clamping device for detecting the clearance of the main control surface of an aircraft provided by this utility model has at least the following advantages and beneficial effects: (1) Based on the principle of measuring the free clearance of the movable surface by loading and measuring the rotation angle, the displacement adjustment component can flexibly adjust the height position of the movable surface clamping mechanism to make the movable surface rotate. By measuring the rotation angle, the free clearance between the movable surface and the stable surface can be accurately obtained, ensuring that the measurement process conforms to the theoretical design and improving the accuracy and reliability of the measurement results; (2) The cooperation between the displacement adjustment component and the movable surface clamping mechanism makes the clearance measurement method of loading and measuring the rotation angle more operable. The loading and rotation angle measurement of the movable surface can be realized without complicated additional devices, simplifying the measurement process, improving the detection efficiency, and reducing the error introduced by complex operation, making the clearance measurement process more convenient and efficient; (3) The ring structure has a certain structural flexibility. With the multi-point arrangement of the lifting block component and real-time force feedback, it can realize the precise clamping and controllable force loading of the clearance of control surfaces with different curvatures, improving the versatility and safety of the device; (4) The clamping device does not require a complicated support structure, which improves stability and reduces the overall weight. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the overall structure of the adaptive clamping device provided in Embodiment 1 of this utility model;

[0032] Figure 2 This is a schematic diagram of the overall structure of the clamping mechanism provided in Embodiment 2 of this utility model;

[0033] Figure 3 This is a schematic diagram of the loading and clamping mechanism provided in Embodiment 2 of this utility model;

[0034] Figure 4 This is a schematic diagram of the locking component in the loading and clamping mechanism provided in Embodiment 2 of this utility model;

[0035] Figure 5 This is a schematic diagram of the movable surface clamping mechanism provided in Embodiment 2 of this utility model;

[0036] Figure 6 This is a schematic diagram of the assembly of the loading clamping mechanism and the tail bracket assembly provided in Embodiment 3 of this utility model;

[0037] Reference numerals: 100-Clamping mechanism, 110-Upper inclined beam assembly, 120-Lower inclined beam assembly, 130-Upper crossbeam, 140-Lower crossbeam, 150-Locking assembly, 151-First handwheel, 152-First base plate, 153-Drive disk, 154-Upper connecting rod, 155-Lower connecting rod, 200-Loading clamping mechanism, 210-Displacement adjustment assembly, 211-Servo motor box, 212-First fixed pulley assembly, 213-First output shaft, 214- Second output shaft, 220-first locking assembly, 221-second handwheel, 230-second locking assembly, 300-movable surface clamping mechanism, 310-rudder surface clamping assembly, 311-third handwheel, 320-first "U"-shaped bracket, 330-second "U"-shaped bracket, 340-crossbar assembly, 341-first crossbar, 342-second crossbar, 400-lifting block assembly, 500-sensor wiring interface, 600-tail hanger assembly. Detailed Implementation

[0038] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. The components of the embodiments of this utility model described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0039] Example 1

[0040] This embodiment provides an adaptive clamping device for detecting the clearance of the main control surfaces of an aircraft. Figure 1 See the overall structural diagram of the adaptive clamping device. Figure 1 As shown, the adaptive clamping device is suitable for measuring the aileron moving surface clearance and the elevator moving surface clearance, and includes a clamping mechanism 100, a loading clamping mechanism 100 and a moving surface clamping mechanism 100.

[0041] The clamping mechanism 100 and the loading clamping mechanism 100 are both U-shaped, and their free ends are connected to form a ring structure. The movable surface clamping mechanism 100 is located inside the ring structure.

[0042] The inner sides of the upper and lower rings of the annular structure are provided with several lifting block assemblies that fit against the stabilizing surface, and the fitting surface of the lifting block assembly is provided with a first pressure sensor.

[0043] The loading clamping mechanism 100 is provided with a displacement adjustment component for adjusting the height position of the movable surface clamping mechanism 100. The clamping mechanism 100 and the loading clamping mechanism 100 are respectively provided with locking components for adjusting and maintaining the clamping state between the lifting block assembly and the stable surface.

[0044] It also includes a control box and a control host, wherein the first pressure sensor is electrically connected to the control box, and the control box is electrically connected to the control host.

[0045] The following describes the installation and fixing of the above-mentioned ring structure:

[0046] The ring structure in the adaptive clamping device is moved from the wingtip position to the clamping position. When it is moved to the designated position, the two sides of the ring structure are locked by adjusting the clamping mechanism 100 and the locking component on the loading clamping mechanism 100 respectively.

[0047] Furthermore, each of the first pressure sensors is connected, and the lifting block assembly is adjusted according to the pressure value transmitted by the first pressure sensors to control the host. The lifting block assembly is then pressed tightly against the stabilizing surface to adapt to the curvature of the clamping position. After the curvature adjustment is completed, the installation and fixation of the annular structure in the adaptive clamping device is completed.

[0048] Specifically, the ring structure has a certain degree of structural flexibility. Combined with the multi-point deployment of lifting support blocks and real-time force feedback, it can achieve precise clamping and controllable force loading of the clearance between control surfaces with different curvatures, thereby improving the versatility and safety of the device.

[0049] The movable surface clamping mechanism 100 has a "U" shaped structure, and a rudder surface clamping assembly that fits into the movable surface is provided on the inner side of the "U" shaped structure. The fitting surface of the rudder surface clamping assembly is provided with a second pressure sensor.

[0050] The displacement adjustment component and the second pressure sensor are both electrically connected to the control box, which is electrically connected to the control host.

[0051] The following describes the installation and fixing of the movable surface clamping mechanism 100:

[0052] The open side of the movable surface clamping mechanism 100 is inserted into the upper and lower sides of the movable surface from the outside of the movable surface. After moving to the designated position, each of the second pressure sensors is turned on. The control surface clamping assembly is adjusted according to the pressure value of the control host uploaded by the second pressure sensor, and the control surface clamping assembly is pressed tightly against the movable surface to complete the installation and fixation of the movable surface clamping mechanism 100.

[0053] In the actual gap measurement process, based on the principle of gap measurement by loading and measuring rotation angle, the displacement adjustment component is activated. The height position of the movable surface clamping mechanism 100 is adjusted by the displacement adjustment component to make the movable surface rotate. The free gap between the movable surface and the stable surface can be accurately obtained by measuring the rotation angle. The displacement adjustment component can provide stable force loading to ensure the accuracy and reliability of the gap measurement results.

[0054] Specifically, the way the displacement adjustment component and the movable surface clamping mechanism 100 work together makes the gap measurement method of loading and measuring rotation angle more operable. It can realize the loading and rotation angle measurement of the movable surface without complicated additional devices, which simplifies the measurement process, improves the detection efficiency, and reduces the error introduced by complex operation, making the gap measurement process more convenient and efficient. In addition, the clamping device does not require a complicated support structure, which improves stability and reduces the overall weight.

[0055] Example 2

[0056] This embodiment, based on the technical solution provided in Embodiment 1, further explains the specific structural design of the ring structure:

[0057] See Figure 2 and Figure 3 As shown, both the clamping mechanism 100 and the loading clamping mechanism 100 include an upper inclined beam group 110, a lower inclined beam group, an upper crossbeam, and a lower crossbeam. The upper inclined beam group 110 and the lower inclined beam group are each composed of two pairs of parallel inclined beams. The upper end of the upper inclined beam group 110 is hinged to the first end of the upper crossbeam, and the clamping mechanism 100 and the second end of the upper crossbeam in the loading clamping mechanism 100 are connected to each other. The lower end of the upper inclined beam group 110 is hinged to the upper end of the lower inclined beam group, and the lower end of the lower inclined beam group is hinged to the first end of the lower crossbeam. The clamping mechanism 100 and the second end of the lower crossbeam in the loading clamping mechanism 100 are connected to each other. The angle between the upper inclined beam group 110 and the lower inclined beam group is acute, and the whole structure is hexagonal.

[0058] In some embodiments, the clamping mechanism 100 and the loading clamping mechanism 100 are each provided with an upper crossbeam and a lower crossbeam. The upper and lower crossbeams of the loading clamping mechanism 100 are long crossbeams, which are used to measure the clearance of the rudder moving surface in conjunction with the tail fin assembly. The upper and lower crossbeams of the clamping mechanism 100 are short crossbeams, but no specific limitation is made here.

[0059] Furthermore, the upper and lower crossbeams are each provided with a sensor wiring interface corresponding to the first pressure sensor; the upper inclined beam assembly 110 pieces and the lower inclined beam assembly are each provided with a sensor wiring interface corresponding to the second pressure sensor. Specifically, the sensor wiring interfaces are provided on the upper crossbeam, lower crossbeam, upper inclined beam assembly 110 pieces, and lower inclined beam assembly, which can greatly organize the sensor wiring harness and avoid the wiring harness from getting tangled during mechanical assembly.

[0060] Regarding the locking components of the clamping mechanism 100 and the loading clamping mechanism 100, since the functions of the clamping mechanism 100 and the loading clamping mechanism 100 are different, the design of the locking components also differs, as detailed below:

[0061] Regarding the locking component on the clamping mechanism 100, in some embodiments, the locking component on the clamping mechanism 100 includes a first handwheel, a first base plate, a drive disk, an upper connecting rod, and a lower connecting rod; wherein, the first base plate is connected between the upper inclined beam group 110 and the lower inclined beam group, and its upper and lower ends are respectively hinged to the upper inclined beam group 110 and the lower inclined beam group; the drive disk is disposed between the parallel inclined beams, the drive disk is provided with a threaded groove, the first handwheel is threadedly engaged with the first base plate, the end of the first handwheel penetrating the first base plate is threadedly engaged with the threaded groove, the upper end of the drive disk is hinged to the first end of the upper connecting rod, the second end of the upper connecting rod is hinged to the upper crossbeam on the inner side of the upper inclined beam group 110, the lower end of the drive disk is hinged to the first end of the lower connecting rod, and the second end of the lower connecting rod is hinged to the lower crossbeam on the inner side of the lower inclined beam group.

[0062] The principle of the locking component on the clamping mechanism 100 is explained below:

[0063] When the locking assembly is in the unlocked state, the upper inclined beam assembly 110 and the lower inclined beam assembly can rotate around the upper and lower ends of the first substrate, thereby adjusting the included angle. Specifically, rotating the handwheel forward engages with the threaded groove at the end of the first substrate, converting the force into a linear direction and driving the drive disc to move linearly towards the inner side of the annular structure. At this time, the first end of the upper and lower connecting rods pushes its second end, increasing the included angle between the upper inclined beam assembly 110 and the inner side of the lower inclined beam assembly. Conversely, rotating the handwheel in the opposite direction engages with the threaded groove at the end of the first substrate, converting the force into a linear direction and driving the drive disc to move linearly towards the outer side of the annular structure. The first end of the upper and lower connecting rods pulls its second end, decreasing the included angle between the upper inclined beam assembly 110 and the inner side of the lower inclined beam assembly.

[0064] The displacement adjustment assembly includes a servo motor box, a first fixed pulley group, a first pull cable, a second fixed pulley group, and a second pull cable; wherein, the servo motor box is connected between the upper inclined beam group 110 and the lower inclined beam group, and its upper and lower ends are respectively hinged to the upper inclined beam group 110 and the lower inclined beam group.

[0065] Specifically, the servo motor housing includes a servo motor, a reducer, and a transmission mechanism. The output shaft of the servo motor is connected to the reducer, and the output shaft of the reducer is connected to the transmission mechanism. The transmission mechanism is used to realize the vertical transformation of the torque direction of the servo motor. The transmission mechanism has a first output shaft located on a first side of the servo motor housing and a second output shaft located on a second side of the servo motor housing. The first side of the servo motor housing is the opposite side of the second side of the servo motor housing. The first fixed pulley group is arranged on the same side as the first output shaft of the transmission mechanism, and the second fixed pulley group is arranged on the same side as the second output shaft of the transmission mechanism. The first end of the first pull cable is connected to the first output shaft of the transmission mechanism, and the second end of the first pull cable is connected to the upper part of the movable surface clamping mechanism 100 via the first fixed pulley group. The first end of the second pull cable is connected to the second output shaft of the transmission mechanism, and the second end of the second pull cable is connected to the lower part of the movable surface clamping mechanism 100 via the second fixed pulley group.

[0066] The following explains the principle of the displacement adjustment component:

[0067] The servo motor inside the servo motor housing starts, and the output shaft drives the reducer to adjust the speed. Through the transmission mechanism, the torque direction is vertically changed, transmitting power to the first and second output shafts respectively. One end of the first cable is connected to the first output shaft, and the other end is connected to the upper part of the movable surface clamping mechanism 100 via the first fixed pulley group (changing the direction of force). One end of the second cable is connected to the second output shaft, and the other end is connected to the lower part of the movable surface clamping mechanism 100 via the second fixed pulley group (changing the direction of force). When the servo motor runs, the transmission mechanism causes the first and second output shafts to rotate, winding and unwinding the first and second cables, thereby precisely pulling the movable surface clamping mechanism 100 up and down, achieving precise adjustment of its height position. This causes the movable surface to rotate, and the free clearance between the movable surface and the stable surface can be accurately obtained by measuring the rotation angle.

[0068] Furthermore, both the first and second pull wires are equipped with tension sensors, which are electrically connected to the control box. Specifically, by acquiring the tension force of the pull wires in real time through the tension sensors, and combining this with the distance from the point of action of the pull wires to the center of rotation of the movable surface, the torque required to rotate the movable surface can be accurately calculated. Based on the principle of measuring the free clearance of the movable surface by loading and measuring the rotation angle, precise torque control makes the rotation of the movable surface more consistent with theoretical expectations, reducing measurement errors caused by torque deviations, thereby improving the accuracy of clearance measurement.

[0069] Both the first and second fixed pulley groups consist of two fixed pulleys, which are respectively located at the upper and lower ends of the inclined beam inside the upper inclined beam group 110 / lower inclined beam group. The tension sensor is set on the tension line between the two fixed pulleys to avoid interference between the tension sensor and the fixed pulleys.

[0070] Regarding the locking component on the loading clamping mechanism 100, see [link to relevant documentation] in some embodiments. Figure 4 As shown, the locking component on the loading clamping mechanism 100 is composed of a first locking component corresponding to the lower inclined beam group and a second locking component corresponding to the upper inclined beam group 110. Both the first locking component and the second locking component include a second handwheel and a second base plate. The second base plate is connected between the parallel inclined beams. The second handwheel is threadedly engaged with the second base plate. The end of the second handwheel that passes through the second base plate abuts against the pivot at the hinge of the upper / lower end of the servo motor box.

[0071] The following explains the principle of the locking component on the loading clamping mechanism 100:

[0072] When the second handwheel is rotated, the rotational motion of the handwheel is converted into linear motion through the thread, so that it passes through the end of the second base plate and abuts against the shaft at the hinge of the upper / lower end of the servo motor box.

[0073] When the second handwheel is tightened, it generates a resisting force on the rotating shaft, increasing the friction at the hinge and thus restricting the rotation of the upper or lower inclined beam assembly 110 around the hinge, achieving locking and maintaining structural stability. When the second handwheel is loosened, the resisting force is eliminated, and the hinge returns to a free rotation state, allowing adjustment of the inclined beam assembly. In this way, the locking component achieves locking and unlocking control of the inclined beam assembly's position, ensuring that the device remains fixed when needed and can be flexibly adjusted.

[0074] For the specific design of the movable surface clamping mechanism 100, see [link to relevant documentation] in some embodiments. Figure 5 As shown, the movable surface clamping mechanism 100 includes a first "U"-shaped bracket, a second "U"-shaped bracket, and a crossbar assembly, forming a basic frame. The free ends of the two "U"-shaped brackets are connected by the crossbar, forming a stable overall structure that provides support for clamping operations.

[0075] The crossbar assembly includes a first crossbar and a second crossbar. The first crossbar is connected between the first free ends of the first "U"-shaped bracket and the second "U"-shaped bracket, and the second crossbar is connected between the second free ends of the first "U"-shaped bracket and the second "U"-shaped bracket.

[0076] The first "U"-shaped bracket and the second "U"-shaped bracket each have a set of opposing rudder surface clamping assemblies on their inner sides. The rudder surface clamping assembly consists of a third handwheel, a third base plate and a second pressure sensor. The third base plate is connected to the free end of the "U"-shaped bracket. The third handwheel is threadedly engaged with the third base plate. The third handwheel extends through the end of the third base plate to the inner side of the "U"-shaped bracket and is connected to the second pressure sensor.

[0077] Specifically, when the third handwheel is rotated, the rotational motion of the handwheel is converted into linear motion through the screw thread, causing it to push the second pressure sensor toward the moving surface through the end of the third substrate. By controlling the amount of rotation of the handwheel, the clamping force can be precisely adjusted; in addition, the second pressure sensor monitors the clamping force in real time and provides feedback, ensuring that the clamping force meets the clamping requirements while avoiding damage to the moving surface.

[0078] In addition, the "U"-shaped bracket also has a sensor wiring interface for installing a second pressure sensor, which can greatly keep the sensor wiring harness neat and prevent the wiring harness from getting tangled during mechanical installation.

[0079] Example 3

[0080] This embodiment is based on the technical solution provided in any one of Embodiments 1 to 2, and provides an adaptive clamping device suitable for measuring the clearance of the rudder moving surface. The adaptive clamping device also includes a tail fin assembly.

[0081] In some implementations, see Figure 6 As shown, the vertical tail pylon assembly includes a first pylon located on the first side of the rudder and a second pylon located on the second side of the rudder. The first end of the first pylon is hinged to the upper crossbeam of the loading clamping mechanism 100, and the first end of the second pylon is hinged to the lower crossbeam of the loading clamping mechanism 100. The second ends of the first pylon and the second pylon are connected to reserved interfaces on both sides of the rudder.

[0082] The following explains the principles of installation and use of the tail support assembly:

[0083] First, install the vertical tail bracket assembly on the reserved interfaces on both sides of the rudder. Remove the lifting block assembly inside the loading clamping mechanism 100 and install it on the vertical tail bracket assembly. Then connect the vertical tail bracket assembly to the long crossbeam of the loading clamping mechanism 100. Adjust the opening of the upper inclined beam assembly 110 and the lower inclined beam assembly by using the second handwheel on the loading clamping mechanism 100. Further connect the first pressure sensor on the lifting block assembly. Adjust the lifting block assembly according to the pressure value fed back to the control host by the first pressure sensor to stably clamp the loading clamping mechanism 100 on the rudder's stabilizing surface.

[0084] Furthermore, the movable surface clamping mechanism 100 is installed and fixed. Unlike the movable surface clamping mechanism 100 provided in Embodiments 1 and 2, in this embodiment, when measuring the clearance of the rudder movable surface, the movable surface clamping mechanism 100 only includes a single "U"-shaped bracket and its matching third handwheel, second pressure sensor, etc. The height position adjustment of the "U"-shaped bracket is changed to the adjustment of the left and right deflection angle, which is the same as the principle of driving the aileron and elevator movable surfaces to rotate through the displacement adjustment component. It will not be described in detail here.

[0085] The above are merely preferred embodiments of this utility model and are not intended to limit the scope of this utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. An adaptive clamping device for detecting the clearance of aircraft main control surfaces, suitable for measuring the clearance of aileron moving surfaces and elevator moving surfaces, characterized in that, It includes a clamping mechanism (100), a loading clamping mechanism (100), and a movable surface clamping mechanism (100); Both the clamping mechanism (100) and the loading clamping mechanism (100) are U-shaped, and their free ends are connected to form a ring structure. The movable surface clamping mechanism (100) is located inside the ring structure. The inner sides of the upper and lower rings of the annular structure are provided with several lifting block assemblies that fit into the stabilizing surface, and the fitting surface of the lifting block assembly is provided with a first pressure sensor. The loading clamping mechanism (100) is provided with a displacement adjustment component for adjusting the height position of the movable surface clamping mechanism (100), and the clamping mechanism (100) and the loading clamping mechanism (100) are respectively provided with locking components for adjusting and maintaining the clamping state between the lifting block assembly and the stable surface; The movable surface clamping mechanism (100) has a "U" shaped structure, and a rudder surface clamping assembly that fits into the movable surface is provided inside the "U" shaped structure. The fitting surface of the rudder surface clamping assembly is provided with a second pressure sensor. It also includes a control box and a control host. The first pressure sensor, the displacement adjustment component and the second pressure sensor are all electrically connected to the control box, and the control box is electrically connected to the control host.

2. The adaptive clamping device for detecting the clearance of aircraft main control surfaces as described in claim 1, characterized in that, Both the clamping mechanism (100) and the loading clamping mechanism (100) include an upper inclined beam group (110), a lower inclined beam group, an upper crossbeam, and a lower crossbeam. The upper inclined beam group (110) and the lower inclined beam group are each composed of two pairs of parallel inclined beams. The upper end of the upper inclined beam group (110) is hinged to the first end of the upper crossbeam, the lower end of the upper inclined beam group (110) is hinged to the upper end of the lower inclined beam group, and the lower end of the lower inclined beam group is hinged to the first end of the lower crossbeam. The angle between the upper inclined beam group (110) and the lower inclined beam group is an acute angle.

3. The adaptive clamping device for detecting the clearance of aircraft main control surfaces as described in claim 2, characterized in that, The locking components on the clamping mechanism (100) include a first handwheel, a first base plate, a drive disk, an upper connecting rod, and a lower connecting rod; The first substrate is connected between the upper inclined beam group (110) and the lower inclined beam group, and its upper and lower ends are respectively hinged to the upper inclined beam group (110) and the lower inclined beam group. The drive disc is arranged between parallel inclined beams. The drive disc is provided with a threaded groove. The first handwheel is threadedly engaged with the first base plate. The end of the first handwheel that passes through the first base plate is threadedly engaged with the threaded groove. The upper end of the drive disc is hinged to the first end of the upper connecting rod. The second end of the upper connecting rod is hinged to the upper crossbeam on the inner side of the upper inclined beam group (110). The lower end of the drive disc is hinged to the first end of the lower connecting rod. The second end of the lower connecting rod is hinged to the lower crossbeam on the inner side of the lower inclined beam group.

4. The adaptive clamping device for detecting the clearance of aircraft main control surfaces as described in claim 2, characterized in that, The displacement adjustment assembly includes a servo motor box, a first fixed pulley group, a first pull cable, a second fixed pulley group, and a second pull cable; The servo motor box is connected between the upper inclined beam group (110) and the lower inclined beam group, and its upper and lower ends are respectively hinged to the upper inclined beam group (110) and the lower inclined beam group. The servo motor housing contains a servo motor, a reducer, and a transmission mechanism. The output shaft of the servo motor is connected to the reducer, and the output shaft of the reducer is connected to the transmission mechanism. The transmission mechanism is used to realize the vertical change of the torque direction of the servo motor. The transmission mechanism has a first output shaft located on the first side of the servo motor housing and a second output shaft located on the second side of the servo motor housing. The first side of the servo motor housing is the opposite side of the second side of the servo motor housing. The first fixed pulley group is arranged on the same side as the first output shaft of the transmission mechanism, and the second fixed pulley group is arranged on the same side as the second output shaft of the transmission mechanism. The first end of the first pull wire is connected to the first output shaft of the transmission mechanism, and the second end of the first pull wire is connected to the upper part of the movable surface clamping mechanism (100) via the first fixed pulley group. The first end of the second pull wire is connected to the second output shaft of the transmission mechanism, and the second end of the second pull wire is connected to the lower part of the movable surface clamping mechanism (100) via the second fixed pulley group.

5. The adaptive clamping device for detecting the clearance of aircraft main control surfaces as described in claim 4, characterized in that, Both the first and second pull wires are equipped with tension sensors, which are electrically connected to the control box.

6. The adaptive clamping device for detecting the clearance of aircraft main control surfaces as described in claim 5, characterized in that, Both the first and second fixed pulley groups consist of two fixed pulleys, which are respectively located at the upper and lower ends of the inclined beam inside the upper inclined beam group (110) / lower inclined beam group. The tension sensor is set on the tension line between the two fixed pulleys.

7. The adaptive clamping device for detecting the clearance of aircraft main control surfaces as described in claim 4, characterized in that, The locking component on the loading clamping mechanism (100) is composed of a first locking component corresponding to the lower inclined beam group and a second locking component corresponding to the upper inclined beam group (110). Both the first locking component and the second locking component include a second handwheel and a second base plate. The second base plate is connected between parallel inclined beams. The second handwheel is threadedly engaged with the second base plate. The end of the second handwheel that passes through the second base plate abuts against the pivot at the hinge of the upper / lower end of the servo motor box.

8. The adaptive clamping device for detecting the clearance of aircraft main control surfaces as described in any one of claims 2 to 7, characterized in that, The movable surface clamping mechanism (100) includes a first "U"-shaped bracket, a second "U"-shaped bracket, and a crossbar assembly; The crossbar assembly includes a first crossbar and a second crossbar. The first crossbar is connected between the first free ends of the first "U"-shaped bracket and the second "U"-shaped bracket, and the second crossbar is connected between the second free ends of the first "U"-shaped bracket and the second "U"-shaped bracket. The first "U"-shaped bracket and the second "U"-shaped bracket each have a set of opposing rudder surface clamping assemblies on their inner sides. The rudder surface clamping assembly consists of a third handwheel, a third base plate and a second pressure sensor. The third base plate is connected to the free end of the "U"-shaped bracket. The third handwheel is threadedly engaged with the third base plate. The third handwheel extends through the end of the third base plate to the inner side of the "U"-shaped bracket and is connected to the second pressure sensor.

9. The adaptive clamping device for detecting the clearance of aircraft main control surfaces as described in claim 8, characterized in that, One or more of the upper crossbeam, lower crossbeam, upper inclined beam assembly (110), lower inclined beam assembly, and "U"-shaped bracket are provided with sensor wiring interfaces.

10. An adaptive clamping device for detecting the clearance of aircraft main control surfaces, comprising the adaptive clamping device for detecting the clearance of aircraft main control surfaces as described in any one of claims 1 to 9, suitable for measuring the clearance of rudder moving surfaces, characterized in that, It also includes the tailstock mounting assembly; The vertical tail pylon assembly includes a first pylon located on the first side of the rudder and a second pylon located on the second side of the rudder. The first end of the first pylon is hinged to the upper crossbeam of the loading clamping mechanism (100), and the first end of the second pylon is hinged to the lower crossbeam of the loading clamping mechanism (100). The second ends of the first pylon and the second pylon are connected to reserved interfaces on both sides of the rudder.

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