Multifunctional tooling device and method for aircraft seat assembly and inspection

Abstract

This invention discloses a multifunctional tooling device and method for aircraft seat assembly and inspection, relating to the field of aircraft seat assembly and inspection technology. The device includes a base, a rotating seat, a seat slide rail mounting bracket, a backrest auxiliary support, a force sensor, an angle sensor, and an intelligent controller. The base can tilt in any direction, the rotating seat rotates about an axis perpendicular to the upper surface of the base, and the backrest auxiliary support can rotate and tilt around the rotating seat. The backrest auxiliary support is equipped with a retractable gripper. The intelligent controller stores preset modes of assembly and inspection parameters for various aircraft seat models and adjusts the base tilt angle, rotating seat rotation angle, backrest auxiliary support tilt angle, and gripper extension length and applied force based on real-time feedback signals from the force and angle sensors. This device can provide assembly assistance in any posture and can also apply multi-directional inspection loads by configuring a counterweight module, achieving multi-purpose functionality and improving aircraft seat assembly efficiency and inspection accuracy.

Description

Technical Field

[0001] This invention relates to the field of aircraft seat assembly and inspection technology, specifically to a multifunctional tooling device and method for aircraft seat assembly and inspection. Background Technology

[0002] As a core component of the aircraft cabin, the assembly quality and structural safety of aircraft seats directly affect flight safety and passenger experience. During aircraft manufacturing and maintenance, aircraft seats undergo precise assembly processes and rigorous performance testing to ensure they meet airworthiness requirements.

[0003] Currently, aircraft seat assembly and testing are typically performed by different specialized equipment, presenting the following technical problems: ① Existing assembly aids are limited in function, unable to adjust the seat's posture at multiple angles, and cannot adapt to the diverse assembly needs of different seat models. ② While existing testing devices offer some angle adjustment, their degrees of freedom are limited, making it impossible to apply controllable forces and torques to the seat simultaneously in multiple degrees of freedom, and thus unable to simulate the multi-posture stress conditions of the seat in actual use. More importantly, existing testing and assembly devices operate independently. After assembly, the seat needs to be transported to a dedicated testing station for inspection, increasing both process and equipment costs. Furthermore, positioning errors during transport may affect the accuracy of the testing results. ③ During aircraft seat assembly, the connection between the backrest and the frame requires precise preload control to ensure connection quality and structural strength. However, the clamping mechanisms of existing assembly aids typically lack force detection and closed-loop control functions, lacking a device for independently applying force and precisely controlling the backrest. Operators rely solely on experience to apply force, making it difficult to guarantee assembly consistency and reliability. ④ Existing assembly and testing equipment is mostly manually operated or simply mechanically controlled, lacking parameterized preset and closed-loop control functions for different types of aircraft seats, making operation complex and inefficient.

[0004] In summary, the existing technology lacks an integrated multi-functional tooling device and method that can simultaneously meet the needs of multi-position assembly assistance and multi-condition structural performance testing of aircraft seats. Summary of the Invention

[0005] The purpose of this invention is to provide a multifunctional tooling device for assembling and inspecting aircraft seats, as well as its assembly and inspection methods, to solve the current technical problems of inefficient and inaccurate assembly and inspection.

[0006] To address the aforementioned technical problems, this invention provides a multifunctional tooling device for aircraft seat assembly and inspection, comprising: A base, wherein the upper surface is configured to be tiltable in any direction; A rotating seat, which is rotatably disposed above the base and configured to rotate about an axis perpendicular to the upper surface of the base; A seat rail mounting bracket is fixedly mounted on the rotating seat and is used to mount the aircraft seat to be processed. A backrest auxiliary bracket is mounted on the rotating seat via a rotatable connector and is located on one side of the seat slide rail mounting bracket. It is configured to tilt about an axis parallel to the rotatable connection between the backrest auxiliary bracket and the rotating seat to accommodate different reclining angles of the aircraft seat's backrest bracket. The backrest auxiliary bracket is provided with a retractable gripper, which is configured to extend and retract in a preset direction to grip the backrest bracket and apply a preload or positioning constraint to the backrest bracket. A force sensor is disposed on the retractable gripper and is used to detect the force applied by the retractable gripper to the backrest support; An angle sensor is disposed on the base, the rotating seat, and the backrest auxiliary bracket, and is used to detect the tilt angle of the upper surface of the base, the rotation angle of the rotating seat, and the tilt angle of the backrest auxiliary bracket. The intelligent controller is communicatively connected to the base, the rotating seat, the backrest auxiliary support, the retractable gripper, the force sensor, and the angle sensor. The intelligent controller is configured to receive feedback signals from the force sensor and the angle sensor, and to control the tilt angle of the upper surface of the base, the rotation angle of the rotating seat, the tilt angle of the backrest auxiliary support, the extension length of the retractable gripper, and the force applied to the backrest support. The intelligent controller has a built-in storage module, which stores preset modes of assembly parameters and preset modes of detection parameters corresponding to the aircraft seat model.

[0007] The multi-functional tooling device for aircraft seat assembly and inspection provides an installation posture suitable for the aircraft seat assembly operation by adjusting the tilt angle of the base, the rotation angle of the rotating seat, and the tilt angle of the backrest auxiliary bracket, and / or applies multi-directional inspection loads to the aircraft seat.

[0008] The present invention also provides an aircraft seat assembly method, comprising the following steps: Step S1: Select the corresponding assembly parameter preset mode according to the model of the aircraft seat to be assembled. The intelligent controller adjusts the tilt angle of the base, the rotation angle of the rotating seat and the tilt angle of the backrest auxiliary bracket according to the preset mode, so that the seat slide rail mounting bracket and the backrest auxiliary bracket are in an installation posture suitable for assembly operation. Step S2: Install the aircraft seat on the seat slide rail mounting bracket. The intelligent controller drives the retractable gripper to extend and grasp the backrest bracket. The preload applied by the retractable gripper is controlled according to the real-time feedback signal of the force sensor. Step S3: Under the preload force, assemble and connect the backrest bracket to the frame of the aircraft seat; Step S4: After assembly, the intelligent controller controls the retractable gripper to release and retract, releasing the backrest bracket.

[0009] The present invention also provides a method for detecting aircraft seats, comprising the following steps: Step D1: Install the aircraft seat to be tested onto the seat slide rail mounting bracket; Step D2: Fix the detection counterweight module to the aircraft seat, and attach the stress and strain measuring device to the surface of the detection counterweight module and / or the part of the aircraft seat to be tested; Step D3: Select the corresponding detection parameter preset mode. The intelligent controller adjusts the tilt angle of the base, the rotation angle of the rotating seat, the tilt angle of the backrest auxiliary bracket, and the extension length and clamping force of the retractable gripper according to the preset mode, and applies the required direction and magnitude of force and torque to the aircraft seat and the backrest bracket. Step D4: The stress-strain measuring device and the force sensor acquire detection data in real time and transmit it to the intelligent controller; Step D5: Change the tilt angle of the base, the rotation angle of the rotating seat, the tilt angle of the backrest auxiliary bracket, the weight of the detection counterweight module, or the extension length of the retractable gripper, and repeat steps D to D to obtain multiple sets of detection data under different poses. Step D6: The intelligent controller automatically generates a test report based on the collected test data.

[0010] The beneficial effects of this invention are as follows: This invention integrates the assembly assistance function and structural performance testing function of an aircraft seat into a single device. Through the coordinated movement of the base tilt adjustment, the rotating seat rotation adjustment, and the backrest auxiliary bracket tilt adjustment, it can provide any required installation posture for the assembly operation and apply multi-directional testing loads to the seat at the same workstation, eliminating the need to transfer the seat between different devices, thus significantly improving production efficiency and equipment utilization. The base of this invention can achieve tilt angle adjustment in any direction, simulating the load direction of an aircraft under different flight attitudes; the rotating seat can rotate around an axis perpendicular to the upper surface of the base, providing load application in any direction within the plane of rotation; the backrest auxiliary bracket can tilt around its rotational connection with the rotating seat, precisely adapting to different reclining angles of the seat back; the three functions work together to simulate the actual stress conditions of an aircraft seat under various flight attitudes such as takeoff, cruise, landing, and emergency landing. This invention applies controllable preload or positioning constraint force to the backrest bracket using retractable grippers. Force sensors mounted on the grippers detect the clamping force in real time, and a smart controller performs closed-loop control to ensure the preload force accurately reaches the set value. This effectively eliminates assembly gaps at the connection between the backrest and the frame, improving assembly accuracy and consistency. The smart controller has a built-in storage module that stores preset assembly and testing parameters for various aircraft seat models. Operators only need to select the corresponding model to automatically complete all adjustments, significantly reducing operational difficulty and human error. Simultaneously, real-time feedback from force and angle sensors enables closed-loop control, ensuring that all parameters accurately reach target values. This invention also includes a data recording and storage module that automatically records and stores parameter data during each assembly or testing process and automatically generates testing reports, providing comprehensive data support for product quality traceability and airworthiness certification. Attached Figure Description

[0011] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a schematic diagram of the overall structure of the multifunctional tooling device for aircraft seat assembly and testing of the present invention. Figure 2 This is a schematic diagram of the base of the present invention (the movable platform is horizontal). Figure 3 This is a schematic diagram of the structure of the base of the present invention (the movable platform is tilted). Figure 4 This is a schematic diagram of the structure of the rotary seat of the present invention; Figure 5 This is a schematic diagram of the structure of the seat slide rail mounting bracket of the present invention; Figure 6 This is a schematic diagram of the backrest auxiliary support of the present invention; Figure 7 This is a schematic diagram of the retractable gripper of the present invention; The meanings of the markings in the diagram are as follows: 1. Base; 11. Fixed base; 12. Movable platform; 13. Tilting drive mechanism; 2. Rotary seat; 21. Lower seat body; 22. Upper seat body; 23. Rotary drive mechanism; 3. Seat slide rail mounting bracket; 31. Slide rail support; 311. Mounting hole; 32. Spacing adjustment mechanism; 4. Backrest auxiliary support; 41. Telescopic gripper; 411. First gripper; 412. Second gripper; 413. Gripper drive mechanism; 414. Gripper head; 42. Column; 43. Telescopic cross arm; 44. Position adjustment mechanism; 46. Hinge seat; 47. Tilting drive mechanism. Detailed Implementation

[0012] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments implemented by those skilled in the art without creative effort are within the protection scope of the present invention.

[0013] Example 1 like Figure 1 As shown, the present invention provides a multi-functional tooling device for aircraft seat assembly and inspection, which mainly includes a base (1), a rotating seat (2), a seat slide rail mounting bracket (3), a backrest auxiliary bracket (4), a force sensor (not shown), an angle sensor (not shown), and an intelligent controller (not shown).

[0014] The base (1) is located at the bottom of the entire device to support all the components above it and is configured to be tilted in any direction.

[0015] Preferably, such as Figure 2 , Figure 3As shown, the specific structure of the base (1) includes a fixed base (11), a movable platform (12), and multiple tilting drive mechanisms (13) connecting the fixed base (11) and the movable platform (12). The multiple tilting drive mechanisms (13) are respectively set at different positions of the fixed base (11), and the tilt angle of the movable platform (12) in any direction can be adjusted by independent extension and retraction. For example, a set of tilting drive mechanisms (13) can be set at the four corners or the middle of the four sides of the fixed base (11). When one or more sets of drive mechanisms extend or retract, the movable platform (12) tilts accordingly in that direction. By controlling the extension and retraction of each drive mechanism, the movable platform (12) can be precisely tilted in any direction.

[0016] The tilting drive mechanism (13) can be any one of a hydraulic cylinder, an electric actuator, a lead screw and nut mechanism, or a worm gear mechanism. In this embodiment, an electric actuator is preferred, which has the advantages of high control accuracy, fast response speed, and convenient maintenance.

[0017] Preferably, the base (1) may also include an angle locking mechanism, which is disposed between the fixed base (11) and the movable platform (12) to lock the movable platform (12) in the current tilt position after the tilt angle of the base (1) is adjusted to the correct position, so as to prevent the angle from changing due to external force during assembly or testing. The angle locking mechanism may adopt a hydraulic lock, mechanical locking claw or electromagnetic brake structure.

[0018] The rotating seat (2) is rotatably disposed above the base (1) and is configured to rotate about an axis perpendicular to the upper surface of the base (1).

[0019] Preferably, such as Figure 4 As shown, the rotating seat (2) includes a lower seat body (21) fixed on the base (1), an upper seat body (22) for supporting the seat slide rail mounting bracket (3), and a rotation drive mechanism (23) disposed between the lower seat body (21) and the upper seat body (22). The upper seat body (22) is driven by the rotation drive mechanism (23) to rotate about an axis perpendicular to the upper surface of the base (1).

[0020] Preferably, the rotary drive mechanism (23) may include a slewing bearing and a rotary drive motor. The slewing bearing can withstand large axial and radial loads, ensuring that the rotating seat (2) can still rotate smoothly when carrying the aircraft seat. The rotary drive motor is preferably a servo motor, which is connected to the upper seat body (22) through a reducer, enabling precise angle control.

[0021] Preferably, the rotating seat (2) is further provided with a rotation locking mechanism, which is used to lock the upper seat (22) in the current rotation position after the rotating seat (2) has rotated to the position. The rotation locking mechanism can be a pin-type locking mechanism or a friction-type locking mechanism to ensure that the rotating seat (2) will not rotate unexpectedly during assembly or testing.

[0022] The seat rail mounting bracket (3) is fixedly mounted on the rotating seat (2) for mounting the aircraft seat to be processed.

[0023] Preferably, such as Figure 5 As shown, the seat rail mounting bracket (3) includes two rail supports (31) arranged parallel to each other on the rotating base (2). Multiple mounting holes (311) are provided on the rail supports (31) for connection to the rails at the bottom of the aircraft seat. The cross-sectional shape of the rail supports (31) and the spacing of the mounting holes (311) can be designed according to common aircraft seat rail standards to ensure compatibility with most aircraft seat models. The seat rail mounting bracket (3) also includes a spacing adjustment mechanism (32) for adjusting the spacing between the two rail supports (31). The spacing adjustment mechanism (32) may include a parallelogram linkage mechanism and a screw-nut mechanism. By rotating the screw, the parallelogram linkage mechanism deforms, thereby causing the two rail supports (31) to move towards or away from each other while maintaining parallelism between the two rail supports (31). Through spacing adjustment and extension adjustment, different models and sizes of aircraft seats can be adapted.

[0024] Preferably, the seat rail mounting bracket (3) may also include a quick-locking mechanism. The quick-locking mechanism is used to quickly install the aircraft seat onto or remove it from the rail support (31). For example, an eccentric cam locking mechanism or a spring snap mechanism may be used to achieve quick clamping and release of the seat.

[0025] Preferably, the seat rail mounting bracket (3) may also include a replaceable rail adapter. The rail adapter is detachably mounted on the rail support (31) to adapt to different standards or specifications of aircraft seat rail interfaces. For example, different series of seat rail interface standards may be different, and by replacing the corresponding rail adapter, the same device can be compatible with different series of aircraft seats.

[0026] The backrest auxiliary bracket (4) is mounted on the rotating base (2) on one side of the seat slide rail mounting bracket (3). It is mounted on the rotating base (2) via a rotating connector and is configured to tilt about an axis parallel to the rotating connection between the backrest auxiliary bracket (4) and the rotating base (2) to accommodate different reclining angles of the aircraft seat backrest bracket. The backrest auxiliary bracket (4) is provided with a retractable gripper (41). The retractable gripper (41) is configured to extend and retract in a specific direction (generally from the backrest auxiliary bracket (4) to the target position of the backrest bracket) to grip the backrest bracket and apply a pre-tightening force or positioning constraint force for auxiliary assembly to the backrest bracket as the backrest auxiliary bracket (4) moves.

[0027] Preferably, such as Figure 6 As shown, the backrest auxiliary support (4) includes a column (42) extending away from the rotating seat (2) and a telescopic cross arm (43) movably mounted on the column (42). A telescopic gripper (41) is located at the end of the telescopic cross arm (43). The backrest auxiliary support (4) is rotatably mounted on the rotating seat (2) via a hinge seat (46). A tilting drive mechanism (47) is provided at the hinge seat (46). The tilting drive mechanism (47) is any one of a hydraulic cylinder, an electric push rod, a screw and nut mechanism, or a worm gear mechanism, used to drive the backrest auxiliary support (4) to tilt about an axis parallel to the rotatable connection between the backrest auxiliary support (4) and the rotating seat (2). In this embodiment, the tilting drive mechanism (47) is preferably a rotary drive motor, preferably a servo motor. The base of the rotary drive motor is mounted on the column (42), and its shaft is connected to the hinge seat (46) via a reducer, which can achieve precise angle control.

[0028] Optionally, the tilting drive mechanism (47) can be an electric push rod, one end of which is hinged to the rotating seat (2) and the other end is hinged to the column (42) of the backrest auxiliary support (4). The backrest auxiliary support (4) is tilted around the hinge seat (46) by the extension and retraction of the electric push rod.

[0029] Preferably, the backrest auxiliary support (4) may also be provided with a tilt locking mechanism, which is used to lock the backrest auxiliary support (4) in the current tilt position after the tilt angle of the backrest auxiliary support (4) is adjusted to the correct position. The tilt locking mechanism may adopt a pin locking or friction locking structure.

[0030] A position adjustment mechanism (44) is provided between the column (42) and the telescopic cross arm (43) to adjust the position of the telescopic gripper (41) along the extension direction of the column (42) and along the extension direction of the telescopic cross arm (43). The position adjustment mechanism (44) includes a height adjustment mechanism and a translation adjustment mechanism. The height adjustment mechanism can adopt a screw-slider mechanism or a cylinder-driven mechanism to raise and lower the telescopic cross arm (43) along the column (42); the translation adjustment mechanism can adopt a slide rail-slider mechanism to move the telescopic cross arm (43) back and forth in the direction perpendicular to the column (42).

[0031] like Figure 7 As shown, the retractable gripper (41) includes a first gripper (411), a second gripper (412), and a gripper drive mechanism (413) for driving the first gripper (411) and the second gripper (412) to open and close relative to each other. The gripper drive mechanism (413) can be any one of a cylinder, a hydraulic cylinder, or a motor. In this embodiment, a motor drive is preferred, which has the advantages of fast response speed and controllable clamping force. The ends of the first gripper (411) and the second gripper (412) have replaceable clamping heads for adapting to backrest supports with different cross-sectional shapes. The clamping surface shape of the clamping head can be V-shaped, arc-shaped, or planar to adapt to backrest supports of different shapes. The operator can select and replace the appropriate clamping head according to the shape of the clamping part of the backrest support to be assembled or inspected, so as to ensure stable clamping and no damage to the workpiece.

[0032] The telescopic gripper (41) extends perpendicularly to the inclined plane of the backrest auxiliary bracket (4). When the backrest auxiliary bracket (4) is tilted, the telescopic gripper (41) also tilts to maintain a perpendicular clamping position with the backrest bracket (101). This linkage design ensures that regardless of the tilt angle of the backrest auxiliary bracket (4), the telescopic gripper (41) can always apply clamping force and preload in a direction perpendicular to the surface of the backrest bracket (101), avoiding unstable clamping or damage to the workpiece due to angular deviation.

[0033] A force sensor is mounted on the retractable gripper (41) to detect the force applied by the retractable gripper (41) to the backrest support.

[0034] Specifically, the force sensor is a pressure sensor disposed on the clamping surface of the retractable gripper (41) or a tension / compression sensor disposed on the drive path of the retractable gripper (41), used to detect in real time the clamping force and / or preload applied by the retractable gripper (41) to the backrest bracket, and to feed back the detection signal to the intelligent controller in real time. When the force sensor is a pressure sensor, it can be disposed on the clamping surfaces of the first gripper (411) and the second gripper (412) respectively to detect the magnitude and distribution of the clamping force. When the force sensor is a tension / compression sensor, it can be disposed on the drive path of the gripper drive mechanism (413) to detect the magnitude of the driving force.

[0035] Angle sensors are installed on the base (1), the rotating seat (2) and the backrest auxiliary bracket (4) to detect the tilt angle of the base (1), the rotation angle of the rotating seat (2) and / or the tilt angle of the backrest auxiliary bracket (4).

[0036] Specifically, the angle sensors include tilt sensors, rotary encoders, and backrest angle sensors.

[0037] An inclination sensor is mounted on the base (1) to detect the tilt angle of the upper surface of the base (1). The inclination sensor can be a dual-axis inclination sensor or a tri-axis inclination sensor, which can simultaneously detect the tilt angle of the base (1) in the front-back direction and the left-right direction.

[0038] A rotary encoder is mounted on a rotary base (2) to detect the rotation angle of the rotary base (2) about an axis perpendicular to the upper surface of the base (1). The rotary encoder can be an absolute encoder or an incremental encoder, and is mounted on the output shaft of the rotary drive mechanism (23) or the rotation shaft of the upper body (22).

[0039] The backrest angle sensor is located at the rotatable connection of the backrest auxiliary bracket (4) and is used to detect the tilt angle of the backrest auxiliary bracket (4) relative to the rotating seat (2). The backrest angle sensor can be a potentiometer-type angle sensor or a magnetoresistive angle sensor.

[0040] The intelligent controller is communicatively connected to the base (1), rotating seat (2), backrest auxiliary support (4), retractable gripper (41), force sensor, and angle sensor. It is configured to receive feedback signals from the force sensor and angle sensor, and control the tilt angle of the base (1), the rotation angle of the rotating seat (2), the tilt angle of the backrest auxiliary support (4), the extension length of the retractable gripper (41), and the force applied to the backrest support. The intelligent controller has a built-in storage module that stores preset modes of assembly parameters and preset modes of detection parameters for various aircraft seat models.

[0041] The device provides an installation posture suitable for aircraft seat assembly operations during assembly by adjusting the tilt angle of the base (1), the rotation angle of the rotating seat (2), and the tilt angle of the backrest auxiliary bracket (4), and applies multi-directional test loads to the aircraft seat during testing.

[0042] As a further improvement of the present invention, the device also includes a detection counterweight module. The detection counterweight module is detachably mounted on the aircraft seat, configured to mimic the shape of a human body, and a stress-strain measuring device is attached to its surface. The stress-strain measuring device is communicatively connected to an intelligent controller and is used to collect real-time stress and deformation data of various parts of the aircraft seat and the detection counterweight module in detection mode.

[0043] Preferably, the counterweight module for testing includes a torso module simulating the human torso, a thigh module simulating the human thigh, and a lower leg module simulating the human lower leg. The torso module, thigh module, and lower leg module are interconnected by hinges, and each hinge is equipped with an angle adjustment mechanism to adjust the relative angle between the modules to simulate different sitting postures. By adjusting the relative angle between the modules, various sitting postures such as upright sitting, semi-reclining sitting, and fully reclining sitting can be simulated, thereby comprehensively evaluating the comfort and safety of the seat under different usage conditions. The torso module, thigh module, and lower leg module are each composed of multiple stacked counterweight blocks, which are detachably connected by a quick-release structure. The counterweight blocks are equipped with an anti-detachment limiting mechanism to prevent them from loosening during testing. By increasing or decreasing the number of counterweight blocks, the load conditions of passengers of different weights can be simulated.

[0044] Pressure sensors are installed on the torso module, thigh module, and calf module, corresponding to the waist, hips, and legs of the human body, respectively. These sensors are used to detect the pressure distribution of different parts of the seat on different parts of the occupant's body, providing data support for seat comfort evaluation.

[0045] Furthermore, the intelligent controller also includes a parameter calling module, a closed-loop control module, a status prompt module, and a data recording and storage module.

[0046] The parameter retrieval module is used to respond to user input operation commands and retrieve the preset mode corresponding to the current aircraft seat model to be processed from the storage module. The preset mode contains the target values ​​of various parameters required for the assembly or testing of the aircraft seat model, including the tilt angle of the base (1), the rotation angle of the rotating seat (2), the tilt angle of the backrest auxiliary bracket (4), the extension length and clamping force of the retractable gripper (41), etc.

[0047] The closed-loop control module is used to adjust the tilt angle of the base (1), the rotation angle of the rotating seat (2), the tilt angle of the backrest auxiliary bracket (4), and the extension length and force of the retractable gripper (41) based on the real-time feedback signals from the force sensor and the angle sensor, until each parameter reaches the target value in the preset mode. The closed-loop control module can use a PID control algorithm or a fuzzy control algorithm to ensure that each parameter converges to the target value quickly and accurately.

[0048] The status prompt module is used to issue a prompt signal when the parameter status of the base (1), rotating seat (2), backrest auxiliary bracket (4), and retractable gripper (41) reaches the target value. The prompt signal can be an audible and visual alarm signal, a text prompt signal on the display screen, or a voice prompt signal.

[0049] The data recording and storage module is used to record and store parameter data during each assembly or inspection process, including the tilt angle of the base (1), the rotation angle of the rotating seat (2), the tilt angle of the backrest auxiliary bracket (4), the extension length and force of the retractable gripper (41), the inspection load data and stress-strain data, and automatically generate inspection reports.

[0050] Preferably, the device further includes a human-machine interface (HMI) that is communicatively connected to the intelligent controller. The HMI can be any one or a combination of a touchscreen display, a button control panel, or a voice control module, used for inputting control commands, displaying real-time status parameters, and outputting detection results. In this embodiment, a touchscreen display is preferred for its intuitive and convenient operation.

[0051] Example 2 This invention provides a method for assembling aircraft seats using the aforementioned multi-functional tooling device for aircraft seat assembly and inspection, comprising the following steps: Step S1: Select the corresponding assembly parameter preset mode according to the model of the aircraft seat to be assembled. The intelligent controller adjusts the tilt angle of the base (1), the rotation angle of the rotating seat (2) and the tilt angle of the backrest auxiliary bracket (4) according to the preset mode, so that the seat slide rail mounting bracket (3) and the backrest auxiliary bracket (4) are in an installation posture suitable for assembly operation.

[0052] For example, when it is necessary to assemble the connecting bolts between the backrest and the frame, the base (1) can be adjusted to an appropriate tilt angle so that the operator can operate in the most comfortable posture; the backrest auxiliary bracket (4) can be adjusted to the same angle as the reclining angle of the backrest bracket so that the gripper (41) can be accurately aligned with the backrest bracket.

[0053] Step S2: Install the aircraft seat on the seat rail mounting bracket (3). The intelligent controller drives the retractable gripper (41) to extend and grasp the backrest bracket. The preload applied by the retractable gripper (41) is controlled according to the real-time feedback signal of the force sensor.

[0054] Preferably, this step specifically includes the following sub-steps: Step S21: The intelligent controller controls the retractable gripper (41) to extend until the retractable gripper (41) contacts the backrest support; Step S22: The intelligent controller reads the real-time detection value of the force sensor and determines whether the current clamping force has reached the target preload value set in the preset mode; Step S23: If the current clamping force does not reach the target preload value, the intelligent controller continues to drive the retractable gripper (41) to extend until the current clamping force reaches the target preload value; Step S24: If the current clamping force has reached the target preload value, the intelligent controller controls the retractable gripper (41) to maintain the current state and issues a prompt signal through the status prompt module.

[0055] Step S3: Assemble and connect the backrest bracket to the aircraft seat frame under preload. Under preload, the gap between the backrest bracket and the frame is eliminated, allowing operators to precisely tighten bolts or rivets.

[0056] Step S4: After assembly, the intelligent controller controls the retractable gripper (41) to release and retract, releasing the backrest support.

[0057] Example 3 This invention provides a method for inspecting aircraft seats using the aforementioned multifunctional tooling device for aircraft seat assembly and inspection, comprising the following steps: Step D1: Install the aircraft seat to be inspected onto the seat rail mounting bracket (3). Generally, the inspection is performed directly after the assembly steps to reduce disassembly and relocation operations.

[0058] Step D2: Install the testing counterweight module on the aircraft seat, and attach the stress-strain measuring device to the surface of the testing counterweight module and the part of the aircraft seat to be tested.

[0059] Step D3: Select the corresponding detection parameter preset mode. The intelligent controller adjusts the tilt angle of the base (1), the rotation angle of the rotating seat (2), the tilt angle of the backrest auxiliary bracket (4), and the extension length and clamping force of the retractable gripper (41) according to the preset mode, and applies the required direction and magnitude of force and torque to the aircraft seat and backrest bracket.

[0060] This step specifically includes the following sub-steps: Step D31: The intelligent controller reads the real-time angle value from the angle sensor and the real-time force value from the force sensor; Step D32: The intelligent controller compares the real-time angle value with the target angle value in the preset mode and the real-time force value with the target force value in the preset mode, respectively; Step D33: If the deviation between the real-time angle value and the target angle value exceeds the preset threshold, the intelligent controller drives the base (1), the rotating seat (2) and / or the backrest auxiliary bracket (4) to move until the real-time angle value reaches the target angle value; Step D34: If the deviation between the real-time force value and the target force value exceeds the preset threshold, the intelligent controller drives the retractable gripper (41) to extend and retract until the real-time force value reaches the target force value.

[0061] Step D4: The stress-strain measurement device and force sensor collect detection data in real time and transmit it to the intelligent controller.

[0062] Step D5: Change the tilt angle of the base (1), the rotation angle of the rotating seat (2), the tilt angle of the backrest auxiliary bracket (4), the weight of the detection counterweight module, and / or the extension length and force of the retractable gripper (41), and repeat steps D3 to D4 to obtain multiple sets of detection data under different poses. By changing multiple parameters, the stress conditions of the aircraft seat under different flight attitudes, different passenger weights, and different sitting postures can be simulated to comprehensively evaluate the structural strength and safety of the seat.

[0063] Step D6: The intelligent controller automatically generates a test report based on the collected test data, providing data support for product acceptance and airworthiness certification.

[0064] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A multi-functional tooling device for aircraft seat assembly and inspection, characterized in that, include: The base (1) is configured such that its upper surface can be tilted at an angle in any direction; Rotary seat (2), which is rotatably disposed above the base (1) and configured to rotate about an axis perpendicular to the upper surface of the base (1); Seat rail mounting bracket (3), which is fixedly mounted on the rotating seat (2) and is used to install the aircraft seat to be processed; A backrest auxiliary bracket (4) is mounted on the rotating seat (2) via a rotating connector and is located on one side of the seat slide rail mounting bracket (3). It is configured to tilt about an axis parallel to the axis at the rotatable connection between the backrest auxiliary bracket (4) and the rotating seat (2) to accommodate different reclining angles of the aircraft seat backrest bracket. A retractable gripper (41) is provided on the backrest auxiliary bracket (4). The retractable gripper (41) is configured to extend and retract in a preset direction to grip the backrest bracket and apply a pre-tightening force or positioning constraint force to the backrest bracket. A force sensor is disposed on the retractable gripper (41) for detecting the force applied by the retractable gripper (41) to the backrest support; An angle sensor is disposed on the base (1), the rotating seat (2) and the backrest auxiliary bracket (4) to detect the tilt angle of the upper surface of the base (1), the rotation angle of the rotating seat (2) and the tilt angle of the backrest auxiliary bracket (4). The intelligent controller is communicatively connected to the base (1), the rotating seat (2), the backrest auxiliary bracket (4), the retractable gripper (41), the force sensor, and the angle sensor. The intelligent controller is configured to receive feedback signals from the force sensor and the angle sensor, and control the tilt angle of the upper surface of the base (1), the rotation angle of the rotating seat (2), the tilt angle of the backrest auxiliary bracket (4), the extension length of the retractable gripper (41), and the force applied to the backrest bracket. The intelligent controller has a built-in storage module, which stores preset modes of assembly parameters and preset modes of detection parameters corresponding to the aircraft seat model.

2. The multi-functional tooling device for aircraft seat assembly and testing according to claim 1, characterized in that, The base (1) includes a fixed base (11), a movable platform (12), and multiple tilting drive mechanisms (13) connected between the fixed base (11) and the movable platform (12). The multiple tilting drive mechanisms (13) are respectively arranged in different positions of the fixed base (11) and the movable platform (12) can be adjusted in any direction by independently extending and retracting.

3. The multi-functional tooling device for aircraft seat assembly and testing according to claim 1, characterized in that, The rotating seat (2) includes a lower seat body (21) fixed on the base (1), an upper seat body (22) for carrying the seat slide rail mounting bracket (3), and a rotary drive mechanism (23) disposed between the lower seat body (21) and the upper seat body (22). The upper seat body (22) is driven by the rotary drive mechanism (23) to rotate about an axis perpendicular to the upper surface of the base (1).

4. The multi-functional tooling device for aircraft seat assembly and testing according to claim 1, characterized in that, The seat slide rail mounting bracket (3) includes two parallel slide rail supports (31) disposed on the rotating seat (2). The slide rail supports (31) are provided with multiple mounting holes (311) for connecting with the bottom slide rail of the aircraft seat. The seat slide rail mounting bracket (3) is also provided with a spacing adjustment mechanism (32) for adjusting the spacing between the two slide rail supports (31).

5. The multi-functional tooling device for aircraft seat assembly and testing according to claim 1, characterized in that, The backrest auxiliary bracket (4) is rotatably mounted on the rotating seat (2) via a hinge seat (46). The hinge seat (46) is provided with a tilting drive mechanism (47) for driving the backrest auxiliary bracket (4) to tilt about an axis parallel to the rotatable connection between the backrest auxiliary bracket (4) and the rotating seat (2).

6. The multi-functional tooling device for aircraft seat assembly and testing according to claim 5, characterized in that, The backrest auxiliary support (4) includes a column (42) extending away from the rotating seat (2) and a retractable horizontal arm (43) movably mounted on the column (42). The retractable gripper (41) is located at the end of the retractable horizontal arm (43). A position adjustment mechanism (44) is provided between the column (42) and the retractable horizontal arm (43) to adjust the position of the retractable gripper (41) along the extension direction of the column (42) and along the extension direction of the retractable horizontal arm (43). The retractable gripper (41) includes a first gripper (411), a second gripper (412), and a gripper drive mechanism (413) for driving the first gripper (411) and the second gripper (412) to open and close relative to each other; the ends of the first gripper (411) and the second gripper (412) have replaceable gripping heads for adapting to backrest supports with different cross-sectional shapes.

7. The multi-functional tooling device for aircraft seat assembly and testing according to claim 1, characterized in that, It also includes a counterweight module for testing, which is detachably mounted on the aircraft seat. The counterweight module is configured to mimic the shape of a human body, and a stress-strain measuring device is attached to the surface of the counterweight module. The stress-strain measurement device is communicatively connected to the intelligent controller and is used to collect stress and deformation data of various parts of the aircraft seat and the counterweight module for testing in real time during the detection mode.

8. The multi-functional tooling device for aircraft seat assembly and testing according to claim 7, characterized in that, The intelligent controller also includes: The parameter retrieval module is used to respond to user input operation commands and retrieve a preset mode corresponding to the current aircraft seat model to be processed from the storage module; The closed-loop control module is used to adjust the tilt angle of the base (1), the rotation angle of the rotating seat (2), the tilt angle of the backrest auxiliary bracket (4), and the extension length and force of the retractable gripper (41) in a closed loop according to the real-time feedback signals of the force sensor and the angle sensor, until each parameter reaches the target value in the preset mode. The status prompt module is used to issue a prompt signal when the parameter status of the base (1), the rotating seat (2), the backrest auxiliary bracket (4) and the retractable gripper (41) reaches the target value; The data recording and storage module is used to record and store parameter data during each assembly or testing process, including the tilt angle of the base (1), the rotation angle of the rotating seat (2), the tilt angle of the backrest auxiliary bracket (4), the extension length and force of the retractable gripper (41), the test load data and stress-strain data, and automatically generate a test report.

9. An aircraft seat assembly method, employing the multi-functional tooling device for aircraft seat assembly and inspection as described in any one of claims 1 to 8, characterized in that, Includes the following steps: Step S1: Select the corresponding assembly parameter preset mode according to the model of the aircraft seat to be assembled. The intelligent controller adjusts the tilt angle of the base (1), the rotation angle of the rotating seat (2) and the tilt angle of the backrest auxiliary bracket (4) according to the preset mode, so that the seat slide rail mounting bracket (3) and the backrest auxiliary bracket (4) are in an installation posture suitable for assembly operation. Step S2: Install the aircraft seat on the seat slide rail mounting bracket (3), the intelligent controller drives the retractable gripper (41) to extend and grasp the backrest bracket, and controls the preload applied by the retractable gripper (41) according to the real-time feedback signal of the force sensor; Step S3: Under the preload force, assemble and connect the backrest bracket to the frame of the aircraft seat; Step S4: After assembly, the intelligent controller controls the retractable gripper (41) to release and retract, releasing the backrest bracket.

10. A method for inspecting aircraft seats, employing the multi-functional tooling device for aircraft seat assembly and inspection as described in claim 7 or 8, characterized in that, Includes the following steps: Step D1: Install the aircraft seat to be tested onto the seat slide rail mounting bracket (3); Step D2: Fix the detection counterweight module to the aircraft seat, and attach the stress and strain measuring device to the surface of the detection counterweight module and / or the part of the aircraft seat to be tested; Step D3: Select the corresponding detection parameter preset mode. The intelligent controller adjusts the tilt angle of the base (1), the rotation angle of the rotating seat (2), the tilt angle of the backrest auxiliary bracket (4), and the extension length and clamping force of the retractable gripper (41) according to the preset mode, and applies the required direction and magnitude of force and torque to the aircraft seat and the backrest bracket. Step D4: The stress-strain measuring device and the force sensor acquire detection data in real time and transmit it to the intelligent controller; Step D5: Change the tilt angle of the base (1), the rotation angle of the rotating seat (2), the tilt angle of the backrest auxiliary bracket (4), the weight of the detection counterweight module, or the extension length of the retractable gripper (41), and repeat steps D3 to D4 to obtain multiple sets of detection data under different poses. Step D6: The intelligent controller automatically generates a test report based on the collected test data.

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