Aviation tensioner with anti-loosening mechanism
By designing the adjustment mechanism and anti-loosening mechanism in the aviation tensioner, the problem of limited adjustment range of the existing tensioner is solved, the practicality of the tensioner and the cargo fixing ability are improved, and the flight safety is ensured.
Patent Information
- Application Number
- CN202420156092.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-01-23
- Publication Date
- 2025-03-21
- Estimated Expiration
- 2034-01-23
AI Technical Summary
The existing tensioners with anti-loosening devices vary in length through the tension sleeve, but the adjustment range is limited, reducing the practicality and applicability of the tensioners.
An aviation tensioner with an anti-loosening mechanism is designed. By setting up an adjustment mechanism and an anti-loosening mechanism, the tightness of the tensioner is adjusted, the adjustment range is increased, and the cargo is prevented from moving and rolling through the anti-loosening mechanism.
It improves the adjustment range and practicality of the tensioner, enhances the fixing ability to cargo, and ensures flight safety.
Smart Images
Figure CN222650478U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of tensioners, in particular to an aviation tensioner with an anti-loosening mechanism. Background Art
[0002] When an airplane takes off, lands, or encounters strong air turbulence during flight, the cargo on the airplane will be affected by inertia and will sway forward, backward, left, and right in an unsteady manner. The magnitude of the impact force depends on the weight of the cargo itself. The heavier the cargo, the greater the impact force, which will have a greater impact on the balance of the airplane during flight. In addition, the impact of air currents on the airplane will seriously affect the balance of the airplane and may cause the airplane to roll over. Therefore, when an airplane is loaded with relatively heavy cargo, it is necessary to take measures to fix the cargo and use a tensioner to fix it in a certain position to prevent the cargo from moving and rolling and affecting flight safety.
[0003] According to the patent with announcement number CN216618411U, a tensioner with an anti-loosening device is proposed. The tensioner with the anti-loosening device can drive the threaded rod to move by rotating the tensioning sleeve, thereby realizing the length change of the entire mechanism. When the tensioning sleeve does not rotate, the two limit sleeves tend to move toward each other, and the threaded rod is clamped by the limit sleeve on the limit hoop. When the limit sleeve presses the limit hoop, multiple deformation grooves on the limit hoop are deformed, so that the limit hoop can increase the friction force on the threaded rod, reduce the probability of movement of the threaded rod, realize the fixation of the relative position of the threaded rod, and increase the stability of the overall mechanism.
[0004] However, the tensioner with an anti-loosening device changes its length through a tensioning sleeve, and the adjustment range is limited, which reduces the practicability and applicability of the tensioner. Therefore, an aviation tensioner with an anti-loosening mechanism is proposed to solve the above problem. Utility Model Content
[0005] In view of the deficiencies in the prior art, the utility model provides an aviation tensioner with an anti-loosening mechanism, which has the advantage of improving the adjustment range of the tensioner and solves the problem that the tensioner with an anti-loosening device changes its length through a tensioning sleeve and has a limited adjustment range, which reduces the practicality and applicability of the tensioner.
[0006] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: an aviation tensioner with an anti-loosening mechanism, comprising a connecting frame, a front side of the connecting frame is provided with an adjusting mechanism for preventing loosening, and a fixed and firmly anti-loosening mechanism is provided inside the adjusting mechanism;
[0007] The adjusting mechanism includes a shell, the back side of which is fixedly connected to the front side of the connecting frame, a first rotating rod having two ends penetrating and extending to the outside thereof is rotatably installed inside the shell, a worm wheel is fixedly installed on the outer surface of the first rotating rod, a worm screw having two ends penetrating and extending to the outside thereof is rotatably installed inside the shell, the outer surface of the worm screw is meshed with the outer surface of the worm wheel, and a locking clip is fixedly installed on the right side of the shell.
[0008] Furthermore, the anti-loosening mechanism includes two fixed lock buckles, the bottoms of the two fixed lock buckles are fixedly connected to the top of the first rotating rod, and the second rotating rod is slidably mounted on the outer surfaces of the two fixed lock buckles.
[0009] Furthermore, mounting holes are provided inside the shell and the connecting frame, and the inner surfaces of the two mounting holes are rotatably connected to the outer surface of the first rotating rod.
[0010] Furthermore, two guide rods are fixedly installed between the front and rear side walls of the inner cavity of the connecting frame, and a mounting rod is fixedly installed between the front and rear side walls of the inner cavity of the connecting frame.
[0011] Furthermore, movable holes are provided on both the left and right sides of the shell, and the inner surfaces of the two movable holes are rotatably connected to the outer surface of the worm.
[0012] Furthermore, the first rotating rod and the second rotating rod are both semicircular in shape when viewed from the front, and the first rotating rod and the second rotating rod are symmetrically distributed on upper and lower sides when viewed from the front.
[0013] Furthermore, a first webbing is fixedly mounted on the outer surface of the mounting rod, and a second webbing is fixedly mounted on the outer surfaces of the first rotating rod and the second rotating rod.
[0014] Furthermore, one end of the first webbing and one end of the second webbing are both fixedly mounted with double-row hooks, and both the first webbing and the second webbing are polyester webbings.
[0015] Compared with the prior art, the technical solution of this application has the following beneficial effects:
[0016] The aviation tensioner with an anti-loosening mechanism achieves the purpose of adjusting the tightness of the tensioner by providing an adjustment mechanism, increases the adjustment range, and improves the practicality and applicability of the tensioner. The anti-loosening mechanism is provided to play a role in installing the webbing, preventing the cargo from moving and rolling and affecting the flight safety. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] Figure 1 It is a schematic diagram of the structure of the utility model;
[0018] Figure 2 The utility model structure Figure 1 A front cross-sectional view of
[0019] Figure 3 The utility model structure Figure 1 Right view of .
[0020] In the figure: 1. connecting frame; 2. adjusting mechanism; 201. housing; 202. first rotating rod; 203. worm gear; 204. worm; 205. locking clip; 206. guide rod; 207. mounting rod; 3. anti-loosening mechanism; 301. fixed locking buckle; 302. second rotating rod; 303. first webbing; 304. second webbing; 305. double-row hook. DETAILED DESCRIPTION
[0021] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0022] Example 1: Please refer to Figure 1 and Figure 2 In this embodiment, an aviation tensioner with an anti-loosening mechanism includes a connecting frame 1, a front side of the connecting frame 1 is provided with an adjusting mechanism 2 to prevent loosening, a fixed anti-loosening mechanism 3 is provided inside the adjusting mechanism 2, the adjusting mechanism 2 includes a shell 201, the back side of the shell 201 is fixedly connected to the front side of the connecting frame 1, a first rotating rod 202 is rotatably installed inside the shell 201 with two ends penetrating and extending to the outside thereof, the shell 201 and the connecting frame 1 are both provided with mounting holes, the inner surfaces of the two mounting holes are rotatably connected to the outer surface of the first rotating rod 202 Then, a worm wheel 203 is fixedly installed on the outer surface of the first rotating rod 202, and a worm 204 with two ends passing through and extending to the outside is rotatably installed inside the outer shell 201. Movable holes are opened on the left and right sides of the outer shell 201. The inner surfaces of the two movable holes are rotatably connected with the outer surface of the worm 204. The outer surface of the worm 204 is meshed with the outer surface of the worm wheel 203. The worm 204 drives the worm wheel 203 and the first rotating rod 202 to rotate. A locking clip 205 is fixedly installed on the right side of the outer shell 201, and the worm 204 is fixed by the locking clip 205.
[0023] Among them, two guide rods 206 are fixedly installed between the front and rear side walls of the inner cavity of the connecting frame 1, and a mounting rod 207 is fixedly installed between the front and rear side walls of the inner cavity of the connecting frame 1.
[0024] Specifically, the worm 204 is rotated by hand, and the worm 204 drives the worm wheel 203 and the first rotating rod 202 to rotate. The first rotating rod 202 drives the second webbing 304 to be wound, and the tightness of the second webbing 304 is adjusted. The worm 204 is fixed by the locking clip 205, which increases the adjustment range and improves the practicality and applicability of the tensioner.
[0025] Example 2: Please refer to Figure 1 and Figure 3 On the basis of the first embodiment, the anti-loosening mechanism 3 includes two fixed lock buckles 301, the bottoms of the two fixed lock buckles 301 are fixedly connected to the top of the first rotating rod 202, and the second rotating rod 302 is slidably installed on the outer surface of the two fixed lock buckles 301. The first rotating rod 202 and the second rotating rod 302 are both semicircular in shape when viewed from the front, and the first rotating rod 202 and the second rotating rod 302 are symmetrically distributed on the upper and lower sides when viewed from the front.
[0026] Among them, the outer surface of the installation rod 207 is fixedly installed with the first webbing 303, the outer surface of the first rotating rod 202 and the outer surface of the second rotating rod 302 are fixedly installed with the second webbing 304, the cargo inside the aircraft cargo hold is fixed by the second webbing 304, the first rotating rod 202 and the second rotating rod 302 are driven by two fixed locks 301 to clamp the second webbing 304, the first rotating rod 202 drives the second webbing 304 to wind, one end of the first webbing 303 and one end of the second webbing 304 are fixedly installed with double-row hooks 305, the first webbing 303 and the second webbing 304 are both polyester webbings, and the second webbing 304 is installed by the first webbing 303 and the double-row hooks 305.
[0027] Specifically, the cargo inside the aircraft cargo hold is fixed by the second webbing 304, which is clamped between the first rotating rod 202 and the second rotating rod 302. The first rotating rod 202 and the second rotating rod 302 are driven by hand through two fixed locks 301 to clamp the second webbing 304, and the second webbing 304 is installed through the first webbing 303 and the double-row hooks 305 to prevent the cargo from moving and rolling and affecting flight safety.
[0028] The working principle of the above embodiment is:
[0029] The cargo inside the aircraft cargo hold is fixed by the second webbing 304, and the second webbing 304 is clamped between the first rotating rod 202 and the second rotating rod 302. The first rotating rod 202 and the second rotating rod 302 are driven by hand through two fixing locks 301 to clamp the second webbing 304, and the second webbing 304 is installed by the first webbing 303 and the double-row hooks 305. The worm 204 is rotated by hand, and the worm 204 drives the worm wheel 203 and the first rotating rod 202 to rotate. The first rotating rod 202 drives the second webbing 304 to wind, and the tightness of the second webbing 304 is adjusted, and the worm 204 is fixed by the lock clamp 205.
[0030] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.
[0031] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. An aviation tensioner with an anti-loosening mechanism, comprising a connecting frame (1), characterized in that: The front of the connecting frame (1) is provided with an adjustment mechanism (2) for preventing loosening, and the interior of the adjustment mechanism (2) is provided with a firmly fixed anti-loosening mechanism (3); The adjusting mechanism (2) comprises a housing (201), the back side of the housing (201) is fixedly connected to the front side of the connecting frame (1), a first rotating rod (202) with two ends passing through and extending to the outside thereof is rotatably mounted inside the housing (201), a worm wheel (203) is fixedly mounted on the outer surface of the first rotating rod (202), a worm (204) with two ends passing through and extending to the outside thereof is rotatably mounted inside the housing (201), the outer surface of the worm (204) is meshed with the outer surface of the worm wheel (203), and a locking clamp (205) is fixedly mounted on the right side of the housing (201).
2. The aviation tensioner with an anti-loosening mechanism according to claim 1, characterized in that: The anti-loosening mechanism (3) comprises two fixed lock buckles (301), the bottoms of the two fixed lock buckles (301) are fixedly connected to the top of the first rotating rod (202), and the second rotating rod (302) is slidably mounted on the outer surfaces of the two fixed lock buckles (301).
3. The aviation tensioner with an anti-loosening mechanism according to claim 1, characterized in that: The housing (201) and the connecting frame (1) are both provided with mounting holes, and the inner surfaces of the two mounting holes are rotatably connected to the outer surface of the first rotating rod (202).
4. The aviation tensioner with an anti-loosening mechanism according to claim 1, characterized in that: Two guide rods (206) are fixedly installed between the front and rear side walls of the inner cavity of the connecting frame (1), and a mounting rod (207) is fixedly installed between the front and rear side walls of the inner cavity of the connecting frame (1).
5. The aviation tensioner with an anti-loosening mechanism according to claim 1, characterized in that: The left and right sides of the housing (201) are both provided with movable holes, and the inner surfaces of the two movable holes are rotatably connected to the outer surface of the worm (204).
6. The aviation tensioner with an anti-loosening mechanism according to claim 2, characterized in that: The first rotating rod (202) and the second rotating rod (302) are both semicircular in shape when viewed from the front, and the first rotating rod (202) and the second rotating rod (302) are symmetrically distributed on the upper and lower sides when viewed from the front.
7. The aviation tensioner with an anti-loosening mechanism according to claim 4, characterized in that: A first webbing (303) is fixedly mounted on the outer surface of the mounting rod (207), and a second webbing (304) is fixedly mounted on the outer surface of the first rotating rod (202) and the outer surface of the second rotating rod (302).
8. The aviation tensioner with an anti-loosening mechanism according to claim 7, characterized in that: One end of the first webbing (303) and one end of the second webbing (304) are both fixedly mounted with double-row hooks (305), and both the first webbing (303) and the second webbing (304) are polyester webbings.