A tensioning mechanism and method of use thereof

Abstract

The present application belongs to the technical field of aircraft calibration, and particularly relates to a bracing mechanism and a method for using the same. The bracing mechanism comprises two bracing components (1), a connecting frame (2) and a quick-mount component (3). The connecting frame (2) is in a T-shaped structure, the two ends of the head of the connecting frame (2) are connected with the two bracing components (1) respectively, the lower end of the rod of the connecting frame (2) is connected with the quick-mount component (3), and the quick-mount component (3) is used for clamping an optical marker.

Description

Technical Field

[0001] This invention belongs to the field of aircraft target calibration technology, specifically relating to a tensioning mechanism and its usage method. Background Technology

[0002] During visual target calibration measurements on aircraft, optical markers must be clamped at specific locations on the aircraft to establish a fixed connection between the optical markers and the aircraft, ensuring that the coordinate system of the optical markers is consistent with the aircraft's coordinate system. To achieve this, the optical markers are typically clamped onto the aircraft, ensuring that their coordinate systems are identical and that there is no change in their positions during calibration. Only under these conditions can the orientation of the aircraft components be accurate. Currently, there are no pre-drilled clamping holes in the optical marker clamping area; therefore, calibration can only be performed by placing the optical markers on the ground, or by disassembling parts of the aircraft and using the holes on the aircraft to fix the optical markers before calibration.

[0003] When there are no pre-reserved clamping holes in the clamping area of ​​the optical marker, there are currently two solutions. The first method is for the operator to place the optical marker on the ground for calibration. The disadvantage of this method is that it cannot meet the requirement of fixing the optical marker to the aircraft, it cannot effectively resist vibration during the calibration process, and the calibration measurement data is inaccurate. The second method is for the operator to remove the aircraft parts to expose the mounting holes, and then clamp the optical marker onto the aircraft to achieve a fixed connection between the optical marker and the aircraft. The disadvantage of this method is that the operator needs to disassemble the aircraft parts, the workload is large, and it takes a long time. Summary of the Invention

[0004] Purpose of the invention: To provide a tensioning mechanism and its usage method to achieve the fixed connection between the optical marker and the aircraft, satisfy the unification of the coordinate system of the optical marker and the coordinate system of the aircraft, and ensure that there is no change in the relative position between the coordinate system of the optical marker and the coordinate system of the aircraft during the target calibration measurement, thereby achieving accurate measurement of the aircraft visual target calibration.

[0005] Technical solution:

[0006] A tensioning mechanism includes: two tensioning components 1, a connecting frame 2, and a quick-release component 3. The connecting frame 2 is a T-shaped structure, including a main support beam 2-1 and a crossbeam 2-3. The upper end of the main support beam 2-1 is connected to the middle of the crossbeam 2-3, and the lower end of the main support beam 2-1 is connected to the quick-release component 3. The quick-release component 3 is used to clamp optical markers. The two ends of the crossbeam 2-3 are respectively connected to the two tensioning components 1 through connecting components. The tensioning component 1 includes: a forward and reverse ratchet 1-1, a tensioning block 1-2, and a first spring 1-3. One end of the first spring 1-3 is in contact with the forward and reverse ratchet 1-1, and the other end of the first spring 1-3 is in contact with the tensioning block 1-2. There are multiple tensioning blocks 1-2 and first springs 1-3, and they correspond one-to-one.

[0007] The connecting components at both ends of the crossbeam 2-3 include: a box-shaped structure, a ratchet rotation shaft 2-4, a ratchet reversing shaft 2-5, two pawls 2-6, two second springs 2-7, three positioning holes 2-8, and a pawl limiting platform. The forward and reverse ratchet 1-1 is mounted on the ratchet rotation shaft 2-4. One end of the pawl 2-6 is set on the side wall of the box-shaped structure via a pin. One end of the second spring 2-7 contacts the side wall of the box-shaped structure, and the other end of the second spring 2-7 contacts the pawl 2-6. The three positioning holes 2-8 are circumferentially distributed and... Corresponding to clockwise, counterclockwise, and fully locked states respectively, the ratchet reversing shaft 2-5 is equipped with a ball plunger 2-9 at one end, and a lever is provided in the middle of the ratchet reversing shaft 2-5 for moving the pawl 2-6 up and down. The pawl limiting platform serves as a dead point 4 to restrict the movement of the pawl 2-6 in the direction of extension of the second spring 2-7. The ball plunger 2-9 cooperates with the positioning hole 2-8 to limit the ratchet reversing shaft 2-5 to the clockwise, counterclockwise, or fully locked states.

[0008] Furthermore, the quick-install component 3 includes a mounting base 3-1, a clamping block 3-2, an insert 3-3, and a straight-handle 3-4. The mounting base 3-1 is connected to the lower end of the main support beam 2-1. A dovetail groove is provided below the mounting base 3-1. The dovetail clamping block 3-2 is placed in the dovetail groove for connection with the optical marker. The insert 3-3 is placed on the side of the dovetail groove. A bolt rod is provided at the end of the straight-handle 3-4. The bolt rod passes through the insert 3-3 to clamp the clamping block 3-2.

[0009] Furthermore, a handle is also provided at the other end of the ratchet reversing shaft 2-5.

[0010] Furthermore, the connecting frame 2 also includes two reinforcing ribs 2-2, wherein one end of the reinforcing rib 2-2 is connected to the middle section of the main support beam 2-1, and the other end of the reinforcing rib 2-2 is connected to the end of the crossbeam 2-3.

[0011] Furthermore, the main support beam 2-1, the reinforcing rib 2-2, and the crossbeam 2-3 are all made of aluminum alloy 2024-T4.

[0012] Furthermore, the surface of the support blocks 1-2 is made of rubber.

[0013] A method of using the above-mentioned tensioning mechanism, the method comprising:

[0014] When not in use, the tensioning component 1 is in the retracted position;

[0015] In use, by moving the ratchet reversing shaft 2-5, the tensioning component 1 moves in the unfolding direction. When the tensioning mechanism is adjusted to be in a specific clamping area, move the ratchet reversing shaft 2-5 to lock the forward and reverse ratchet 1-1, and the tensioning mechanism is fixed to the aircraft.

[0016] An optical marker is installed on the tensioning mechanism, at which point the tensioning mechanism is fully locked on the aircraft.

[0017] Beneficial effects:

[0018] The present invention provides a tensioning mechanism that is fixed to an aircraft by means of tensioning. One end of the mechanism is tensioned to the aircraft, and the other end is clamped to an optical marker, thereby realizing the fixed connection between the optical marker and the aircraft and solving the problem that the optical marker cannot be fixed to the aircraft due to the lack of reserved holes in the clamping area.

[0019] This invention allows operators to easily attach optical markers to aircraft without complicated procedures. In use, the operator opens the tensioning mechanism, secures it to the aircraft, and fixes the optical marker at the other end, thus solving the problems of existing technologies. Attached Figure Description

[0020] Figure 1(a) is a schematic diagram of the working state of the tensioning mechanism;

[0021] Figure 1(b) is a schematic diagram of the tensioning mechanism in its contracted state;

[0022] Figure 2(a) is a front view of the tensioning mechanism structure;

[0023] Figure 2(b) is a side view of the tensioning mechanism structure;

[0024] Figure 3 Diagram showing the counter-clockwise movement of the supporting components;

[0025] Figure 4 Diagram showing the clockwise movement of the supporting components;

[0026] Figure 5 The diagram shows the component completely jammed to ensure it is properly secured.

[0027] Figure 6 Schematic diagram of the working principle of the ratchet reversing shaft;

[0028] Figure 7 This is the state when the ratchet reversing shaft is in contact with the lower pawl;

[0029] Figure 8 This is the state when the ratchet reversing shaft is in contact with the upper pawl;

[0030] Figure 9 This is the state when the ratchet reversing shaft and the pawl are not in contact.

[0031] Figure 10 Axonometric drawing of the quick-assembly component;

[0032] Figure 11 Axonometric drawing of the tensioning mechanism.

[0033] The components include: tensioning component 1, connecting frame 2, quick-install component 3, forward and reverse ratchet 1-1, tensioning block 1-2, first spring 1-3, main support beam 2-1, reinforcing rib 2-2, crossbeam 2-3, ratchet rotation shaft 2-4, ratchet reversing shaft 2-5, pawl 2-6, second spring 2-7, positioning hole 2-8, ball plunger 2-9, mounting base 3-1, clamping block 3-2, insert 3-3, flathead hand-tightening handle 3-4, and dead point 4. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0035] In the description of this invention, it should be understood that the terms "center", "axial", "vertical", "upper", "lower", "upper end", "bottom end", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this invention.

[0036] This invention relates to a clamping technique for optical markers used in aircraft visual target calibration. Specifically, this invention discloses a clamping mechanism that enables the quick installation of optical markers onto the aircraft even when there is no pre-reserved standard installation position for the optical markers during aircraft visual target calibration measurements, thereby ensuring accurate measurement of aircraft visual targets.

[0037] As shown in Figure 1(a) to Figure 11 As shown, the tensioning mechanism of the present invention includes: a tensioning component 1, a connecting frame 2, and a quick-release component 3. The tensioning component 1 includes a forward and reverse ratchet 1-1, a tensioning block 1-2, and a first spring 1-3. The connecting frame 2 includes: a main support beam 2-1, a reinforcing rib 2-2, a crossbeam 2-3, a ratchet rotation shaft 2-4, a ratchet reversing shaft 2-5, a pawl 2-6, and a second spring 2-7. The quick-release component 3 includes: a mounting base 3-1, a clamping block 3-2, an insert 3-3, and a flathead hand-tightening handle 3-4.

[0038] Figure 1(a) shows the state when the tensioning component 1 is tensioned, and Figure 1(b) shows the state when the tensioning component 1 is retracted. The tensioned state is the working state of the tensioning component 1, and the retracted state is the retraction of the tensioning component 1 to reduce the space occupied.

[0039] There are two sets of tensioning components 1, which are symmetrically installed on the connecting frame 2. The tensioning components 1 and the connecting frame 2 are connected by a ratchet structure. The quick-release components 3 are bolted to the connecting frame 2. The quick-release components 3 are used to clamp optical markers.

[0040] The connecting frame 2 has a T-shaped structure, with the two ends of the head connected to two tensioning parts 1 via connecting components, and the lower end of the rod used to clamp optical markers.

[0041] The two ends of the tensioning component 1 are a forward and reverse ratchet 1-1 and a tensioning block 1-2, respectively. The forward and reverse ratchet 1-1 adopts a forward and reverse ratchet structure, which can realize the forward and reverse rotation of the tensioning component 1. The connecting frame 2 and the quick-release component 3 are connected by bolts. The quick-release component 3 is used to clamp optical markers. Optical markers can be quickly clamped by turning the handle 3-4.

[0042] The forward and reverse ratchet 1-1 adopts a forward and reverse ratchet structure, and its forward and reverse rotation is achieved by the action of the ratchet reversing shaft 2-5. The support block 1-2 has a large contact surface with the aircraft, and high-temperature resistant rubber is adhered to the contact area between the support block 1-2 and the aircraft. The high-temperature resistant rubber has a mesh-like structure at the contact area, resulting in a high coefficient of friction. One end of the first spring 1-3 contacts the forward and reverse ratchet 1-1, and the other end contacts the support block 1-2. There are multiple support blocks 1-2 and one-to-one correspondences between the first springs 1-3 and the first springs 1-3. The first springs 1-3 are stainless steel compression springs, which can dampen shocks and absorb impact forces. Through the deformation of the first spring 1-3 and the flexible deformation of the high-temperature resistant rubber in the support block 1-2, the tightening process ensures that it will not damage the aircraft surface.

[0043] As shown in the structural schematic diagrams of the connecting frame 2 in Figures 2(a) and 2(b), the upper end of the main support beam 2-1 is connected to the middle of the crossbeam 2-3, and the lower end of the main support beam 2-1 is used to clamp optical markers. Both ends of the crossbeam 2-3 are connected to two tensioning components 1 via connecting assemblies. The connecting assemblies at both ends of the crossbeam 2-3 include: a box-shaped structure, a ratchet rotation shaft 2-4, a ratchet reversing shaft 2-5, two pawls 2-6, two second springs 2-7, three positioning holes 2-8, and a pawl limiting platform. The forward and reverse ratchet 1-1 is mounted on the ratchet rotation shaft 2-4; one end of the pawl 2-6 is set on the side wall of the box-shaped structure via a pin, one end of the second spring 2-7 contacts the side wall of the box-shaped structure, and the other end of the second spring 2-7 contacts the pawl 2-6; the three positioning holes 2-8 are circumferentially distributed and... Corresponding to clockwise, counterclockwise, and fully locked states, the ratchet reversing shaft 2-5 has a ball-head plunger 2-9 at one end and a lever in the middle for moving the pawl 2-6 up and down. A pawl limiting platform serves as a dead point 4 to restrict the movement of the pawl 2-6 towards the extension direction of the second spring 2-7. The ball-head plunger 2-9 engages with the positioning hole 2-8 to limit the ratchet reversing shaft 2-5 to the clockwise, counterclockwise, or fully locked state. A handle is also provided at the other end of the ratchet reversing shaft 2-5.

[0044] The connecting frame 2 also includes two reinforcing ribs 2-2, wherein one end of the reinforcing rib 2-2 is connected to the middle section of the main support beam 2-1, and the other end of the reinforcing rib 2-2 is connected to the end of the crossbeam 2-3.

[0045] The main support beam 2-1, reinforcing rib 2-2, and crossbeam 2-3 are all made of 2024-T4 aluminum alloy, a general aviation material. The connecting frame 2 adopts a lightweight design. Through simulation analysis and engineering experience, the shape of the connecting frame 2 is optimized while ensuring product functionality. Sufficient thickness is ensured in the support or installation parts, or reinforcing ribs are added. Holes are cut in non-load-bearing parts to reduce weight, resulting in a thinner frame. This achieves both strength and rigidity requirements while reducing weight. The forward and reverse ratchet 1-1 is mounted on the ratchet rotation shaft 2-4, which is installed at the end of the crossbeam 2-3. The ratchet reversing shaft 2-5 is mounted on the main support beam 2-1. The forward and reverse rotation of the ratchet 1-1 is achieved by manually rotating the ratchet reversing shaft 2-5.

[0046] The mounting base 3-1 and the insert 3-3 are in the form of a dovetail groove. The optical marker comes with its own insert 3-3. After the insert 3-3 is clamped onto the mounting base 3-1, tighten the flathead handle 3-4 to clamp the optical marker. Mounting base 3-1 is connected to main support beam 2-1 via hex bolts. Main support beam 2-1, reinforcing rib 2-2, and crossbeam 2-3 are connected by bolts. Ratchet rotation shaft 2-4 and ratchet reversing shaft 2-5 are mounted on crossbeam 2-3. Forward and reverse ratchet 1-1 is mounted on ratchet rotation shaft 2-4. Ratchet reversing shaft 2-5, pawl 2-6, and second spring 2-7 allow for forward and reverse rotation of ratchet 1-1 by rotating ratchet reversing shaft 2-5, pawl 2-6, and second spring 2-7. First spring 1-3 is mounted on forward and reverse ratchet 1-1. When tensioning block 1-2 is tightened, tensioning component 1 is unfolded. After being tightened on the aircraft, the optical marker is clamped onto quick-release component 3, further tightening tensioning component 1 on the aircraft. This structure is simple overall, easy to operate, and allows for quick clamping of optical markers on the aircraft without the need for additional tools.

[0047] Figure 3 This is a diagram of the tensioning component of the present invention. At this time, the forward and reverse ratchet 1-1 can only rotate counterclockwise. Figure 3 The diagram illustrates the structure of the forward and reverse ratchet 1-1, the support block 1-2, the first spring 1-3, the ratchet reversing shaft 2-5, the pawl 2-6, and the second spring 2-7. At this time, the ratchet reversing shaft 2-5 moves downward, opening the pawl 2-6 below. The forward and reverse ratchet 1-1 can rotate counterclockwise, but it is jammed when rotating clockwise downward (at dead point 4). It is also jammed when rotating clockwise.

[0048] Figure 4 The diagram shows the tensioning component of this invention. At this time, the forward and reverse ratchet 1-1 can only rotate clockwise. The ratchet reversing shaft 2-5 moves upward, opening the upper pawl 2-6, allowing the forward and reverse ratchet 1-1 to rotate clockwise, while it is locked in the counter-clockwise direction.

[0049] Figure 5 This is a diagram of the tensioning component of the present invention. At this time, the forward and reverse ratchet 1-1 is in a jammed state. At this time, the ratchet reversing shaft 2-5 moves to a horizontal state, and both the upper and lower pawls 2-6 are in contact with the forward and reverse ratchet 1-1, so the forward and reverse ratchet 1-1 is completely jammed.

[0050] Figure 6 This is a schematic diagram illustrating the locking of the ratchet reversing shaft 2-5 according to the present invention. A positioning hole 2-8 is provided on the crossbeam 2-3, and a ball-head plunger 2-9 is mounted on the ratchet reversing shaft 2-5. By rotating the ratchet reversing shaft 2-5, the ball-head plunger 2-9 engages with different positioning holes 2-8. This allows the ratchet reversing shaft 2-5 to be in different positions, thus placing the forward and reverse ratchet 1-1 in different states.

[0051] Ratchet reversing shaft 2-5 rotates to Figure 7When (for easier observation, the crossbeam 2-3 is hidden), and the ratchet reversing shaft 2-5 contacts the pawl 2-6 below, the tensioning component 1 can move counterclockwise. (Refer to...) Figure 3 .

[0052] Ratchet reversing shaft 2-5 rotates to Figure 8 When (for easier observation, the crossbeam 2-3 is hidden), and the ratchet reversing shaft 2-5 contacts the upper pawl 2-6, the tensioning component 1 can move clockwise. (See reference.) Figure 4 .

[0053] Ratchet reversing shaft 2-5 rotates to Figure 9 When (for easier observation, the crossbeam 2-3 is hidden), and the ratchet reversing shaft 2-5 is not in contact with the upper and lower pawls 2-6, the tensioning component 1 is completely locked. (Refer to...) Figure 5 .

[0054] The quick-install component 3 adopts a dovetail groove design. The mounting base 3-1 is connected to the main support beam 2-1 by bolts, ensuring a secure and reliable fixation. The insert 3-3 is used to install optical markers. Manually tightening the flathead handle 3-4 clamps the clamping block 3-2, completing the clamping of the optical markers. The mounting base 3-1 is connected to the lower end of the main support beam 2-1. A dovetail groove is provided below the mounting base 3-1, and the dovetail-shaped clamping block 3-2 is placed in the dovetail groove for connection with the optical markers. The insert 3-3 is located on the side of the dovetail groove, and a bolt rod is provided at the end of the flathead handle 3-4. The bolt rod passes through the insert 3-3 to clamp the clamping block 3-2.

[0055] When not in use, the tensioning component 1 is in the retracted state, reducing the space occupied (see Figure 1(b)). In use, by moving the ratchet reversing shaft 2-5, the tensioning component 1 moves in the unfolding direction. After adjusting to the unfolded state, moving the ratchet reversing shaft 2-5 locks the forward and reverse ratchet 1-1. After clamping the entire mechanism at a specific clamping area, the tensioning mechanism is fixed to the aircraft. Optical markers are then installed on it, and at this time, the tensioning mechanism is completely locked on the aircraft.

[0056] Preferably, a forward and reverse ratchet mechanism is used in the unfolded and retracted states. The forward and reverse ratchet structure is a gap-moving structure composed of a forward and reverse ratchet 1-1, a ratchet rotation shaft 2-4, a ratchet reversing shaft 2-5, and a pawl 2-6. Locking the forward and reverse ratchet 1-1 can prevent reverse rotation.

[0057] Preferably, the upper end of the quick and stable tensioning mechanism of the tensioning component 1 will be more tightened when the optical marker is clamped under downward pressure. The tensioning blocks 1-2 adopt an ultra-anti-slip, widened and lengthened rubber base to increase the friction force.

[0058] Preferably, the first spring 1-3 is selected from suitable springs to ensure that it provides appropriate force and will not damage the aircraft surface due to the hard contact between the tensioning mechanism and the aircraft. The first spring 1-3 can absorb and reduce the impact and vibration applied to the structure. Due to the flexibility of the rubber itself, it can adapt to the magnitude of the force through compression, providing better stability.

[0059] Compared with existing methods, this invention has a simple structure, is easy to clamp, and is firmly fixed to the aircraft, which can meet the requirements of the optical marker coordinate system and the aircraft coordinate system.

[0060] Compared to the existing test method 1, where the optical marker is placed on the ground and not fixed to the aircraft, it cannot effectively resist vibration during the calibration process, resulting in inaccurate calibration measurement data. The structure adopted in this invention is completely fixed to the aircraft, which can unify the coordinate system of the optical marker with the coordinate system of the aircraft. Moreover, the fixed connection between the structure and the aircraft is firm and reliable, and will not cause deviation between the coordinate system of the optical marker and the coordinate system of the aircraft due to interference from external factors, thus meeting the requirements for accurate measurement of aircraft visual calibration.

[0061] Compared to the existing testing method 2, where operators disassemble aircraft components to expose mounting holes for clamping optical markers, this method is complex, time-consuming, and labor-intensive. The structure used in this invention is completely fixed to the aircraft, eliminating the need to disassemble aircraft components. This ensures the consistency between the coordinate system of the optical marker and the aircraft coordinate system. Furthermore, the structure is simple to operate, easy to clamp, and convenient to disassemble after measurement. It requires minimal manpower and time to complete the clamping of optical markers, enabling accurate measurement of aircraft visual target calibration.

[0062] In summary, the clamping mechanism of this invention can fix the optical marker to the aircraft, ensuring the consistency between the coordinate system of the optical marker and the aircraft coordinate system. During measurement, it avoids the influence of other factors on the coordinate system. In aircraft visual target calibration, it eliminates the need to disassemble existing aircraft parts, allowing for quick and stable installation of the optical marker even in specific areas of the aircraft without clamping holes, thus achieving accurate measurements during aircraft visual target calibration. One end of the clamping mechanism is clamped in a specific area of ​​the aircraft, while the other end clamps the optical marker.

[0063] 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 tensioning mechanism, characterized in that, include: Two tensioning components, a connecting frame, and a quick-release component are provided. The connecting frame has a T-shaped structure and includes a main support beam and a crossbeam. The upper end of the main support beam is connected to the middle of the crossbeam, and the lower end of the main support beam is connected to the quick-release component. The quick-release component is used to clamp optical markers. The two ends of the crossbeam are connected to the two tensioning components through connecting components. The tensioning component includes: a forward and reverse ratchet, a tensioning block, and a first spring. One end of the first spring contacts the forward and reverse ratchet, and the other end contacts the tensioning block. There are multiple tensioning blocks and one-to-one corresponding first springs. The connecting components at both ends of the crossbeam include: a box-shaped structure, a ratchet rotation shaft, a ratchet reversing shaft, two pawls, two second springs, three positioning holes, and a pawl limiting platform. The forward and reverse ratchet is mounted on the ratchet rotation shaft. One end of the pawl is mounted on the side wall of the box-shaped structure via a pin. One end of the second spring contacts the side wall of the box-shaped structure, and the other end of the second spring contacts the pawl. The three positioning holes are circumferentially distributed and correspond to clockwise, counterclockwise, and fully locked states, respectively. A ball-head plunger is provided at one end of the ratchet reversing shaft, and a lever is provided in the middle of the ratchet reversing shaft for moving the pawl up and down. The pawl limiting platform serves as a dead point to restrict the movement of the pawl in the direction of the second spring's extension. The ball-head plunger cooperates with the positioning holes to limit the ratchet reversing shaft to the clockwise, counterclockwise, or fully locked state.

2. The tensioning mechanism according to claim 1, characterized in that, The quick-installation components include a mounting base, a clamping block, an insert, and a flat-top handle. The mounting base is connected to the lower end of the main support beam. A dovetail groove is provided below the mounting base, and the dovetail-shaped clamping block is placed in the dovetail groove for connection with optical markers. The insert is located on the side of the dovetail groove, and a bolt rod is provided at the end of the flat-top handle. The bolt rod passes through the insert to clamp the clamping block.

3. The tensioning mechanism according to claim 1, characterized in that, A handle is also provided at the other end of the ratchet reversing shaft.

4. The tensioning mechanism according to claim 1, characterized in that, The connecting frame also includes two reinforcing ribs, one end of which is connected to the middle section of the main support beam, and the other end of which is connected to the end of the crossbeam.

5. The tensioning mechanism according to claim 1, characterized in that, The main support beam, stiffeners, and crossbeams are all made of aluminum alloy 2024-T4.

6. The tensioning mechanism according to claim 1, characterized in that, The surface of the support block is made of rubber.

7. A method of using the tensioning mechanism as described in any one of claims 1-6, characterized in that, The method includes: When not in use, the tensioning components are in the retracted position; In use, the ratchet reversing shaft structure is turned to move the tensioning component in the unfolding direction. When the tensioning mechanism is adjusted to be in a specific clamping area, the ratchet reversing shaft is turned to lock the forward and reverse ratchet, and the tensioning mechanism is then fixed to the aircraft. An optical marker is installed on the tensioning mechanism, at which point the tensioning mechanism is fully locked on the aircraft.

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