Variable sling stroke coupling attitude adjustment device

Abstract

This application provides a variable sling stroke coupling attitude adjustment device, belonging to the field of aircraft drop test technology. It includes a device housing, a screw-pulley power assembly, a support frame, a guide auxiliary pulley assembly, a fixed pulley assembly, slings, and a vertical guide assembly. The support frame is fixed inside the device housing, and its horizontal cross-section is an X-shaped structure. The four corners of the top of the support frame are connected to a load-bearing frame. The vertical guide assembly is located at the middle of the top of the support frame. The screw-pulley power assembly is located at the top of each branch of the X-shaped structure. Fixed pulley assemblies and guide auxiliary pulley assemblies are installed on the side walls of each branch. Four slings are provided, one end of which is connected to the test aircraft body, and the other end of each sling is connected to the lifting power source via the screw-pulley power assembly, guide auxiliary pulley assembly, fixed pulley assembly, and vertical guide assembly. This application features a high degree of automation, increasing the efficiency and accuracy of the test aircraft's attitude adjustment while reducing labor costs.

Description

Technical Field

[0001] This application relates to the field of aircraft drop test technology, and in particular to a variable sling stroke coupled attitude adjustment device. Background Technology

[0002] Full-scale drop tests of carrier-based aircraft are a core technical means to study and verify the structural resistance to carrier / landing impacts. By simulating key parameters such as aircraft attitude, weight, lift, descent speed, and yaw speed during carrier landing, the test assesses the impact resistance of the airframe structure and the reliability of onboard systems / equipment. During a full-scale drop test, the aircraft is raised to a predetermined height and released with a specific pitch / roll attitude, replicating the landing conditions on an aircraft carrier deck. The aircraft attitude adjustment device is a critical piece of equipment in the full-scale drop test; its performance directly affects the safety, reliability, and accuracy of the test, while the aircraft attitude adjustment speed directly impacts the test efficiency and schedule.

[0003] Existing attitude adjustment devices mainly include the following types: the fuselage vest-type attitude adjustment device used in the F-35C full-aircraft drop test, and the single-point four-sling attitude adjustment device. The fuselage vest-type attitude adjustment device relies on an external frame mounted on the fuselage to adjust the aircraft's attitude. The frame mainly consists of electric push rods, sliding rails, and other devices. Attitude adjustment is achieved by adjusting the position of the lifting point. The problem is that when facing large-span structures such as rotating radomes at the center of gravity, the fuselage vest's mounting position interferes with the fuselage, and the added mass is too large to be acceptable. The single-point four-sling attitude adjustment device adjusts the aircraft's pitch and roll attitude by controlling the lengths of four slings at one lifting point. However, this sling adjustment method relies on manual labor, resulting in limited accuracy and efficiency in attitude adjustment, and it also fails to solve the structural interference problem. In terms of cost and efficiency, single-point four-sling attitude adjustment devices mostly rely on manual labor, that is, the attitude adjustment is completed by the installer manually adjusting the length of the slings, which is inefficient and makes it difficult to guarantee the accuracy of the aircraft attitude adjustment; fuselage vest-type attitude adjustment devices mainly rely on high-precision control systems, which are costly and have excessive added mass. Summary of the Invention

[0004] In view of this, the present application provides a variable sling stroke coupling attitude adjustment device, which at least partially solves the problems of low efficiency and low adjustment accuracy of manual adjustment of sling length in the prior art.

[0005] This application provides a variable sling stroke coupling attitude adjustment device. The device includes a housing, a screw pulley power assembly, a support frame, a guide auxiliary pulley assembly, a fixed pulley assembly, slings, and a vertical guide assembly. The support frame is fixed inside the housing and is configured as a frame structure with an X-shaped cross-section in the horizontal direction. The four corners of the top of the support frame are connected to the load-bearing frame. The vertical guide assembly is located at the middle of the top of the support frame and is used to adjust the lateral or oblique direction of the sling to a vertical direction. The screw pulley power assembly is located at the top of each branch of the X-shaped structure. Fixed pulley assemblies and guide auxiliary pulley assemblies are provided on the side walls of each branch of the X-shaped structure. There are four slings. One end of each sling is connected to the test machine body, and the other end of each sling is connected to the lifting power source through the screw pulley power assembly, guide auxiliary pulley assembly, fixed pulley assembly, and vertical guide assembly. The screw pulley power assembly is used to dynamically adjust the effective suspension length of the sling.

[0006] According to a specific implementation of this application, the lead screw pulley power assembly includes a base plate, a servo motor, a lead screw assembly, a linear guide rail, and a movable pulley assembly. The movable pulley assembly includes a movable pulley body located at the bottom. The base plate is set at the top of each branch of the X-shaped structure. The servo motor is set at one end of the base plate, and the linear guide rail is set at the other end of the base plate. The linear guide rail is laid parallel to both sides of the base plate along the long axis direction. The base plate between the two linear guide rails is hollowed out. The top of the movable pulley assembly is slidably connected to the linear guide rail. One end of the lead screw assembly is set on the upper side of the top of the movable pulley assembly, and the other end of the lead screw assembly is connected to the servo motor. The other end of the lead screw assembly is fixed to the base plate by a fixing seat. The bottom of the movable pulley assembly passes through the hollowed-out area, and the movable pulley body is located on the lower side of the base plate. The movable pulley body is provided with a rope groove matching the outer diameter of the sling.

[0007] According to a specific implementation of an embodiment of this application, the movable pulley assembly further includes a bearing connecting frame, which includes a flange plate and two bearing plates. The two bearing plates are vertically connected to the lower side of the flange plate. The lower surface of the flange plate is slidably connected to the linear guide rail via a slider. The slider is fixed on the lower surface of the flange plate. The upper surface of the flange plate is connected to the lead screw assembly. The movable pulley body is fixed between the two bearing plates via a force-bearing pin assembly.

[0008] According to a specific implementation of an embodiment of this application, the lead screw pulley power assembly further includes a coupling, and the servo motor is connected to the lead screw assembly through the coupling.

[0009] According to a specific implementation of an embodiment of this application, the lead screw pulley power assembly further includes a reduction gearbox, which includes a planetary reducer and a worm gear reducer. The output shaft of the servo motor is connected to one end of the planetary reducer, the other end of the planetary reducer is connected to one end of the worm gear reducer, and the other end of the worm gear reducer is connected to a coupling.

[0010] According to a specific implementation of an embodiment of this application, the vertical guide assembly includes four main guide pulleys, four pulley supports, and a support base plate. The support base plate is connected to the middle position of the top of the support frame. The four pulley supports are disposed on the support base plate, and the main guide pulleys are disposed on the pulley supports. One main guide pulley corresponds to one pulley support. A through hole is provided on the support base plate next to each pulley support. The sling passes through the through hole and then through the main guide pulley to connect with the lifting power source.

[0011] According to a specific implementation of this application, each through hole is provided with an auxiliary limiting pulley on its upper side. After the sling passes through the through hole, it passes through the auxiliary limiting pulley and the main directional pulley in sequence, and then connects to the lifting power source.

[0012] According to a specific implementation of an embodiment of this application, the fixed pulley assembly includes an outer fixed pulley, a middle fixed pulley, and an inner fixed pulley. The outer fixed pulley is located at the edge of the side wall of each branch of the X-shaped structure and corresponds to the lifting point of the test body. The inner fixed pulley is close to the vertical guide assembly. The middle fixed pulley is located between the outer fixed pulley and the inner fixed pulley. The sling passes sequentially through the outer fixed pulley, the middle fixed pulley, the movable pulley assembly, the inner fixed pulley, and the vertical guide assembly.

[0013] According to a specific implementation of the present application, a reinforcing rib is provided at the connection between the bearing plate and the flange plate, and an anti-rotation baffle is provided at the end of the force-bearing pin assembly.

[0014] According to a specific implementation of this application, the support frame is fixed inside the device housing by connecting pins, and connecting ears are provided at the four corners of the top of the support frame, so that the posture adjustment device as a whole is connected to the support frame by the connecting ears.

[0015] Beneficial effects:

[0016] The variable sling stroke coupling attitude adjustment device in this embodiment adopts a four-sling structure, which can solve the attitude adjustment problem of the whole aircraft drop test with large lateral span devices such as rotating radar domes; the attitude adjustment is achieved by changing the length of the sling through the pulley driven by the servo motor, which has a high degree of automation and eliminates the need for manual adjustment, greatly increasing efficiency and reducing labor costs; the attitude adjustment accuracy is greatly improved by adjusting the sling stroke through the control of the lead screw transmission accuracy by the servo motor. Attached Figure Description

[0017] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a structural diagram of a variable sling stroke coupling attitude adjustment device according to an embodiment of the present invention; Figure 2 This is an internal structural diagram of a variable sling stroke coupling attitude adjustment device according to an embodiment of the present invention; Figure 3 This is a structural diagram of a lead screw pulley power assembly according to an embodiment of the present invention; Figure 4 This is a structural diagram of a movable pulley assembly according to an embodiment of the present invention; Figure 5 This is a structural diagram of a vertical guide assembly according to an embodiment of the present invention; Figure 6 This is a schematic diagram of the sling routing according to an embodiment of the present invention; Figure 7 This is a schematic diagram of a gearbox structure according to an embodiment of the present invention; Figure 8 This is a schematic diagram of aircraft attitude adjustment according to an embodiment of the present invention; Figure 9 This is a schematic diagram of the overall device layout according to an embodiment of the present invention.

[0019] In the diagram: 01, bearing frame; 02, test machine body; 03, variable sling stroke coupling attitude adjustment device; 0, device shell; 1, lead screw pulley power assembly; 2, support frame; 3, guide auxiliary pulley assembly; 4, fixed pulley assembly; 5, sling; 6, connecting pin; 7, vertical guide assembly; 8, connecting lug; 11, servo motor; 12, coupling; 13, lead screw assembly; 14, linear guide rail; 15, slider; 16, movable pulley assembly; 17, fixed seat; 18, base plate; 19, gearbox; 41. Outer fixed pulley; 42. Middle fixed pulley; 43. Inner fixed pulley; 51. First sling; 52. Second sling; 53. Third sling; 54. Fourth sling; 71. Main directional pulley; 72. Pulley support; 73. Auxiliary limiting pulley; 74. Bearing base plate; 161. Bearing connecting frame; 162. Moving pulley body; 163. Force-bearing pin assembly; 164. Reinforcing rib; 165. Rope groove; 166. Anti-rotation baffle; 191. Planetary reducer; 192. Worm gear reducer. Detailed Implementation

[0020] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0021] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0022] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using structures and / or functionalities other than one or more of the aspects set forth herein.

[0023] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The illustrations only show the components related to this application and are not drawn according to the number, shape and size of the components in actual implementation. In actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0024] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0025] In one embodiment, a variable sling travel coupling attitude adjustment device 03 is provided, referring to... Figure 1 and Figure 2The device includes a housing 0, a lead screw and pulley power assembly 1, a support frame 2, a guide auxiliary pulley assembly 3, a fixed pulley assembly 4, a sling 5, and a vertical guide assembly 7. The support frame 2 is fixed inside the housing 0 and is configured as a frame structure. The horizontal cross-section of the support frame 2 is X-shaped. The four corners of the top of the support frame 2 are connected to the load-bearing frame 01. The vertical guide assembly 7 is located at the middle of the top of the support frame 2 and is used to adjust the horizontal or diagonal routing direction of the sling 5 to a vertical direction. The screw pulley power assembly 1 is set at the top of each branch of the X-shaped structure. The fixed pulley assembly 4 and the guide auxiliary pulley assembly 3 are set on the side wall of each branch of the X-shaped structure. There are four slings 5. One end of each sling 5 is connected to the test body 02. The sling 5 serves as the direct bearing medium. The other end of each sling 5 is connected to the lifting power source through the screw pulley power assembly 1, the guide auxiliary pulley assembly 3, the fixed pulley assembly 4 and the vertical guide assembly 7. The screw pulley power assembly 1 is used to dynamically adjust the effective suspension length of the sling 5.

[0026] In practical implementation, the variable sling stroke coupled attitude adjustment device 03 effectively avoids the interference problem between the sling and the structure when adjusting the attitude of aircraft with large lateral spans such as rotating radomes, through its lateral large span configuration. After removing the outer shell 0, the variable sling stroke coupled attitude adjustment device 03 mainly includes a screw pulley power assembly 1, a support frame 2, a guide auxiliary pulley assembly 3, a fixed pulley assembly 4, a sling 5, and a vertical guide assembly 7. The screw pulley power assembly 1 can dynamically adjust the effective suspension length of the sling 5. In this device, four sets of screw pulley power assemblies 1 are usually symmetrically arranged. By controlling the relative length difference between each set of slings 5, the test aircraft 02 can be precisely adjusted to the specified pitch and roll angles, thereby simulating the initial attitude of the aircraft under different landing conditions.

[0027] The support frame 2 is the core load-bearing frame 01 of the overall device. Through high-rigidity welding or integral machining, it aims to provide a stable installation space for all moving parts and withstand the enormous static and dynamic loads during lifting. The fixed pulley assembly 4 is rigidly fixed at specific stress points on the support frame 2, and its main function is to change the direction of force transmission of the sling 5. To ensure operational reliability, the variable sling stroke coupling attitude adjustment device 03 is also equipped with a guide auxiliary pulley assembly 3. This assembly consists of multiple small fixed pulleys, set close to the running path of the sling 5. Its core function is to work in conjunction with the fixed pulley assembly 4 to limit the sling 5 at multiple points, ensuring that the sling 5 remains constrained within the pulley grooves during high-speed retraction or drastic attitude changes, thus eliminating the safety hazards caused by the sling 5 jumping out of its grooves.

[0028] In one embodiment, refer to Figure 3The lead screw and pulley power assembly 1 includes a base plate 18, a servo motor 11, a lead screw assembly 13, a linear guide rail 14, and a movable pulley assembly 16. The movable pulley assembly 16 includes a movable pulley body 162 located at the bottom. The base plate 18 is set at the top of each branch of the X-shaped structure. The servo motor 11 is set at one end of the base plate 18, and the linear guide rail 14 is set at the other end of the base plate 18. The linear guide rail 14 is laid parallel to the long axis of the base plate 18 on both sides of the base plate 18. The base plate 18 is hollowed out. The top of the movable pulley assembly 16 is slidably connected to the linear guide rail 14. One end of the lead screw assembly 13 is located on the top side of the movable pulley assembly 16. The other end of the lead screw assembly 13 is connected to the servo motor 11. The other end of the lead screw assembly 13 is fixed to the base plate 18 through the fixing seat 17. The bottom of the movable pulley assembly 16 passes through the hollowed-out area. The movable pulley body 162 is located on the lower side of the base plate 18. The movable pulley body 162 is provided with a rope groove 165 that matches the outer diameter of the sling 5.

[0029] In practice, the screw pulley power assembly 1 drives the high-precision ball screw to rotate through the servo motor, converting the rotational motion into the linear displacement of the moving pulley assembly 16. By changing the position of the moving pulley assembly 16 in the horizontal axis, the effective suspension length of the sling 5 is dynamically adjusted.

[0030] The four lead screw pulley power assemblies 1 are fixed on the support frame 2. The overall configuration of the support frame 2 is determined by the positional relationship of the lower wire rope lifting points. It can be understood that the position of the lifting points on the aircraft determines the position of the sling 5, which in turn determines the configuration of the support frame 2, and thus the angular relationship between the lead screw pulley power assemblies 1. In one embodiment, the angle between two adjacent lead screw pulley power assemblies 1 is 14°.

[0031] Furthermore, the lead screw pulley power assembly 1 also includes a coupling 12, through which the servo motor 11 is connected to the lead screw assembly.

[0032] In practical implementation, the lead screw and pulley power assembly 1, as the core of the entire aircraft drop test attitude adjustment system, adopts a high-precision transmission architecture. This assembly, with the base plate 18 as the connecting transition plate, consists of a servo motor 11, coupling 12, lead screw assembly 13, linear guide rail 14, slider 15, movable pulley assembly 16, fixed seat 17, and reduction gearbox 19. The assembly relationship and mechanical transmission logic of each component are as follows: Servo motor 11, as the power source of the system, is responsible for driving the system's operation and, through its built-in feedback module, monitors the speed and angular displacement data, providing remote attitude adjustment data reference. The gearbox 19 primarily amplifies the output torque of servo motor 11 to overcome heavy lifting loads. Simultaneously, through self-locking, it ensures that the tension of the sling 5 cannot reverse the motor's rotation when the system is powered off or under static load conditions, thus guaranteeing the safety of heavy-load suspension. Coupling 12 serves as a connecting component, compensating for installation errors between the output shaft of servo motor 11 and the lead screw shaft, and absorbing torsional impacts during motor start-up and shutdown.

[0033] After the power is transmitted to the lead screw assembly 13 via the coupling 12, the lead screw converts the rotational torque into a linear push-pull force. The fixed seat 17 serves to fix the lead screw assembly 13. In terms of guidance, two high-precision linear guide rails 14 are fixed in parallel on the base plate 18, and four sliders 15 are mounted on them. The moving pulley assembly 16 below is fixed to the sliders 15 by bolts.

[0034] The movable pulley assembly 16 reciprocates in a straight line in the horizontal direction along with the load-bearing slide plate. By changing its physical coordinate system position, it directly pulls and changes the effective extension and retraction stroke of the sling 5. The base plate 18 serves as a transition connector, and its lower side is connected to the support frame 2 by high-strength bolts, smoothly transmitting the reaction force generated by the entire actuator to the main load-bearing frame 01.

[0035] Furthermore, refer to Figure 4 The movable pulley assembly 16 also includes a support connecting frame 161, which includes a flange plate and two support plates. The two support plates are vertically connected to the lower side of the flange plate. The lower surface of the flange plate is slidably connected to the linear guide rail 14 via a slider 15. The slider 15 is fixed on the lower surface of the flange plate. The upper surface of the flange plate is connected to the lead screw assembly 13. The movable pulley body 162 is fixed between the two support plates via a force-bearing pin assembly 163.

[0036] Specifically, the movable pulley body 162 functions to change the effective winding stroke of the sling 5, achieving linear fine-tuning of the aircraft's attitude. The movable pulley body 162 has a rope groove 165 on its circumference that matches the outer diameter of the sling 5, increasing the contact area and reducing wear on the sling 5. The load-bearing connecting frame 161 adopts a U-shaped integral load-bearing structure with oblique reinforcing ribs 164. Mounting holes are machined on the top flange plate for bolting to the movable slider 15 below the flange plate. The load-bearing pin assembly 163 is the core load-bearing component that withstands dual shear forces. The end of the load-bearing pin assembly 163 is specially designed with an anti-rotation baffle 166 structure, which reduces the risk of axial movement of the pin under vibration and restricts its own circumferential rotation, avoiding wear caused by pin rotation.

[0037] Furthermore, refer to Figure 7The lead screw pulley power assembly 1 also includes a reduction gearbox 19, which includes a planetary reducer 191 and a worm gear reducer 192. The output shaft of the servo motor 11 is connected to one end of the planetary reducer 191, the other end of the planetary reducer 191 is connected to one end of the worm gear reducer 192, and the other end of the worm gear reducer 192 is connected to the coupling 12.

[0038] In practical implementation, the main function of planetary reducer 191 is to reduce speed and increase output torque, while achieving efficient and stable power transmission. The main function of worm gear reducer 192 is to cooperate with planetary reducer 191 to achieve power transmission, and it also has a self-locking function to lock the spatial position of the lead screw pulley power assembly 1, thereby ensuring the stability of the aircraft's attitude. Planetary reducer 191 and servo motor 11, as well as planetary reducer 191 and worm gear reducer 192, are all connected by keys.

[0039] In one embodiment, refer to Figure 5 and Figure 6 The vertical guide assembly 7 includes four main guide pulleys 71, four pulley supports 72, and a support base plate 74. The support base plate 74 is connected to the middle position of the top of the support frame 2. The four pulley supports 72 are set on the support base plate 74, and the main guide pulleys 71 are set on the pulley supports 72. One main guide pulley 71 corresponds to one pulley support 72. A through hole is provided on the support base plate 74 next to each pulley support 72. The sling 5 passes through the through hole and passes through the main guide pulley 71 to connect with the lifting power source.

[0040] Furthermore, each through hole is provided with an auxiliary limiting pulley 73 on its upper side. After the sling 5 passes through the through hole, it passes through the auxiliary limiting pulley 73 and the main guide pulley 71 in sequence, and then connects to the lifting power source.

[0041] In practical implementation, the vertical guide component 7 functions to uniformly convert the lateral or diagonal routing of the sling 5 into a vertical lifting force. The structural features and engineering functions of each component are as follows: The bearing base plate 74 serves as the load-bearing foundation of this component. Its structure is an integrally machined plate with numerous through holes on its surface. The lower surface of the bearing base plate 74 is reliably fixed to the support frame 2, and the upper surface of the bearing base plate 74 is fixed to the pulley support 72.

[0042] The pulley support 72 is fastened to the bearing base plate 74 via the flange face at the bottom. Considering the overturning moment that will occur during reversal, the outer side of the vertical plate of the pulley support 72 is designed with structural reinforcing ribs 164 to improve bending stiffness. The main directional pulley 71 is installed at the top of the pulley support 72. Its main function is to receive the non-vertical sling 5 from the downstream. By using the wrap angle constraint of the pulley groove, the tension vector direction of the sling 5 is deflected to the positive vertical direction, thereby eliminating the lateral component force applied to the test body 02.

[0043] At the moment of impact, the sling 5 is prone to high-frequency lateral swaying. Therefore, auxiliary limiting pulleys 73 are installed at key load-bearing points around it. The auxiliary limiting pulleys 73, together with the main directional pulley 71, provide multi-dimensional spatial constraint on the sling 5. Simultaneously, they convert the sliding friction between the sling 5 and the base plate hole wall at the turning point into rolling friction with the limiting pulleys, thereby preventing cutting damage to the edges of the sling 5 and improving test safety.

[0044] Furthermore, refer to Figure 6 The fixed pulley assembly 4 includes an outer fixed pulley 41, a middle fixed pulley 42, and an inner fixed pulley 43. The outer fixed pulley 41 is located at the edge of the side wall of each branch of the X-shaped structure and corresponds to the lifting point of the test body 02. The inner fixed pulley 43 is close to the vertical guide assembly 7. The middle fixed pulley 42 is located between the outer fixed pulley 41 and the inner fixed pulley 43. The sling 5 passes through the outer fixed pulley 41, the middle fixed pulley 42, the movable pulley assembly 16, the inner fixed pulley 43, and the vertical guide assembly 7 in sequence.

[0045] In specific implementation, the position of the outer fixed pulley 41 is determined according to the lifting point on the aircraft; the position of the middle fixed pulley 42 must be closer to the middle of the support frame 2 than the screw pulley power assembly 1, so as to ensure that the screw pulley power assembly 1 plays a role throughout its entire screw stroke; the position of the inner fixed pulley 43 is in the middle and rear part of the inner fixed pulley 43. The routing of the sling 5 in the overall device is as follows: Figure 6 As shown (some auxiliary pulleys omitted), the fixed pulley assembly 4 consists of three fixed pulleys: an outer fixed pulley 41, a middle fixed pulley 42, and an inner fixed pulley 43. The position of the outer fixed pulley 41 is determined by the lifting point of the aircraft. The sling 5 moves upward along the lifting point, first passing over the outer fixed pulley 41, then over the middle fixed pulley 42, and connects to the movable pulley assembly 16. After the movable pulley body 162 moves, the position of the sling 5 is as shown... Figure 6 As shown in the dashed line, the sling 5, which passes around the movable pulley assembly 16, finally passes around the inner fixed pulley 43 and connects to the vertical guide assembly 7. Under the action of the auxiliary limiting pulley 73 and the main guiding pulley 71, the direction is restricted to the direction of the plumb bob and finally connected to the upper lifting power source.

[0046] In one embodiment, a reinforcing rib 164 is provided at the connection between the bearing plate and the flange plate, and an anti-rotation baffle 166 is provided at the end of the load-bearing pin assembly 163. The reinforcing ribs 164 on both sides of the bearing connecting frame 161 are designed to improve the overall bending stiffness of the support and can effectively prevent the bearing plate from expanding outward or yielding under large loads.

[0047] In one embodiment, the support frame 2 is fixed inside the device housing 0 by connecting pins 6, and connecting ear seats 8 are provided at the four corners of the top of the support frame 2, so that the posture adjustment device is connected to the bearing frame 01 by the connecting ear seats 8.

[0048] Specifically, the connecting pin 6 serves two purposes: firstly, as a positioning pin, ensuring precise alignment and rapid fastening between the support frame 2 and the device housing 0; secondly, as a lateral structural reinforcement, effectively improving the torsional resistance of the entire device under high loads and preventing overall structural instability and deformation due to uneven stress. The connecting lug 8 serves as an interface, reliably connecting the entire attitude adjustment device to the external load-bearing frame 01.

[0049] In one embodiment, reference Figure 8 and Figure 9 The aircraft attitude adjustment procedure is as follows: The main control system reads and confirms the preset target attitude information, and calculates the required displacement target amount for the four suspension points through kinematic attitude. After the command is issued, the four servo motors 11 start synchronously. By controlling the rotation angle of the motors, the lead screw assembly 13 is driven to rotate, thereby converting the rotational power into the forward and backward linear displacement of the movable pulley assembly 16 on the guide rail. As the movable pulley assembly 16 moves, the upper sling 5 continuously changes its length for lowering or tightening based on the stroke ratio of the pulley, thereby changing the absolute position of each suspension point on the machine body.

[0050] To achieve decoupled control of spatial attitude, the system employs a cross-group differential adjustment method: when adjusting the aircraft's pitch attitude, the control system primarily performs differential control on the two sets of slings 5 ​​along the aircraft's heading, causing the two front slings 5 ​​(second sling 52 and fourth sling 54) and the two rear slings 5 ​​(first sling 51 and third sling 53) to undergo opposite length changes, thereby generating a pitch moment around the aircraft's center of gravity. Similarly, when adjusting the aircraft's roll attitude, the system switches to a lateral linkage mode, constructing a roll moment by controlling the relative extension difference between the two sets of slings 5 ​​along the aircraft's sides (the first and second slings 52 on the left and the third and fourth slings 53 on the right). Through the differential adjustment of the lengths of the four slings 5, this attitude adjustment device can lock the spatial attitude of the test aircraft 02 at the target attitude.

[0051] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A variable sling stroke coupling attitude adjustment device, characterized by, The device includes a housing (0), a screw pulley power assembly (1), a support frame (2), a guide auxiliary pulley assembly (3), a fixed pulley assembly (4), a sling (5), and a vertical guide assembly (7). The support frame (2) is fixed inside the housing (0) and is configured as a frame structure. The horizontal cross-section of the support frame (2) is configured as an X-shaped structure. The four corners of the top of the support frame (2) are connected to the load-bearing frame (01). The vertical guide assembly (7) is located at the middle of the top of the support frame (2) and is used to guide the horizontal or diagonal routing of the sling (5). The direction is adjusted to be vertical. The screw pulley power assembly (1) is set at the top of each branch of the X-shaped structure. The fixed pulley assembly (4) and the guide auxiliary pulley assembly (3) are set on the side wall of each branch of the X-shaped structure. There are four slings (5). One end of each sling (5) is connected to the test machine body (02). The other end of each sling (5) is connected to the lifting power source after passing through the screw pulley power assembly (1), the guide auxiliary pulley assembly (3), the fixed pulley assembly (4) and the vertical guide assembly (7). The screw pulley power assembly (1) is used to dynamically adjust the effective suspension length of the sling (5).

2. The variable sling stroke coupling attitude adjustment device according to claim 1, characterized in that, The lead screw pulley power assembly (1) includes a base plate (18), a servo motor (11), a lead screw assembly (13), a linear guide rail (14), and a movable pulley assembly (16). The movable pulley assembly (16) includes a movable pulley body (162) located at the bottom. The base plate (18) is set at the top of each branch of the X-shaped structure. The servo motor (11) is set at one end of the base plate (18), and the linear guide rail (14) is set at the other end of the base plate (18). The linear guide rail (14) is laid parallel to the long axis of the base plate (18) on both sides of the base plate (18). The base plate (18) between them is hollowed out. The top of the movable pulley assembly (16) is slidably connected to the linear guide rail (14). One end of the lead screw assembly (13) is set on the top side of the movable pulley assembly (16). The other end of the lead screw assembly (13) is connected to the servo motor (11). The other end of the lead screw assembly (13) is fixed on the base plate (18) through the fixing seat (17). The bottom of the movable pulley assembly (16) passes through the hollowed-out area. The movable pulley body (162) is located on the lower side of the base plate (18). The movable pulley body (162) is provided with a rope groove (165) that matches the outer diameter of the sling (5).

3. The variable sling stroke coupling attitude adjustment device according to claim 2, characterized in that, The movable pulley assembly (16) also includes a load-bearing connecting frame (161), which includes a flange plate and two load-bearing plates. The two load-bearing plates are vertically connected to the lower side of the flange plate. The lower surface of the flange plate is slidably connected to the linear guide rail (14) via a slider (15). The slider (15) is fixed on the lower surface of the flange plate. The upper surface of the flange plate is connected to the lead screw assembly (13). The movable pulley body (162) is fixed between the two load-bearing plates via a force-bearing pin assembly (163).

4. The variable sling stroke coupling attitude adjustment device according to claim 2, characterized in that, The lead screw pulley power assembly (1) also includes a coupling (12), through which the servo motor (11) is connected to the lead screw assembly.

5. The variable sling stroke coupling attitude adjustment device according to claim 4, characterized in that, The lead screw pulley power assembly (1) also includes a gearbox (19), which includes a planetary reducer (191) and a worm gear reducer (192). The output shaft of the servo motor (11) is connected to one end of the planetary reducer (191), and the other end of the planetary reducer (191) is connected to one end of the worm gear reducer (192). The other end of the worm gear reducer (192) is connected to the coupling (12).

6. The variable sling stroke coupling attitude adjustment device according to claim 1, characterized in that, The vertical guide assembly (7) includes four main guide pulleys (71), four pulley supports (72), and a support plate (74). The support plate (74) is connected to the middle of the top of the support frame (2). The four pulley supports (72) are set on the support plate (74), and the main guide pulleys (71) are set on the pulley supports (72). One main guide pulley (71) corresponds to one pulley support (72). A through hole is provided on the support plate (74) next to each pulley support (72). The sling (5) passes through the through hole and then through the main guide pulley (71) to connect with the lifting power source.

7. The variable sling stroke coupling attitude adjustment device according to claim 6, characterized in that, Each through hole is provided with an auxiliary limiting pulley (73) on the upper side. After the sling (5) passes through the through hole, it passes through the auxiliary limiting pulley (73) and the main guide pulley (71) in sequence, and then connects to the lifting power source.

8. The variable sling stroke coupling attitude adjustment device according to claim 1, characterized in that, The fixed pulley assembly (4) includes an outer fixed pulley (41), a middle fixed pulley (42) and an inner fixed pulley (43). The outer fixed pulley (41) is located at the edge of the side wall of each branch of the X-shaped structure and corresponds to the lifting point of the test body (02). The inner fixed pulley (43) is close to the vertical guide assembly (7). The middle fixed pulley (42) is located between the outer fixed pulley (41) and the inner fixed pulley (43). The sling (5) passes through the outer fixed pulley (41), the middle fixed pulley (42), the movable pulley assembly (16), the inner fixed pulley (43) and the vertical guide assembly (7) in sequence.

9. The variable sling stroke coupling attitude adjustment device according to claim 3, characterized in that, The connection between the bearing plate and the flange plate is provided with a reinforcing rib (164), and the end of the force-bearing pin assembly (163) is provided with an anti-rotation baffle (166).

10. The variable sling stroke coupling attitude adjustment device according to claim 1, characterized in that, The support frame (2) is fixed inside the outer shell (0) of the device by connecting pins (6). The four corners of the top of the support frame (2) are respectively provided with connecting ear seats (8), and the posture adjustment device is connected to the bearing frame (01) by connecting ear seats (8).

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