Fixing and locking frame for twelve-tube aircraft flame strip spreading device
By enhancing the stability of the locking block connection through structures such as limiting devices and rubber strips, the problem of aircraft flame spreaders loosening during vibration is solved, thus improving safety.
Patent Information
- Application Number
- CN202520038614.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-08
- Publication Date
- 2025-12-30
- Estimated Expiration
- 2035-01-08
AI Technical Summary
The locking structure of existing aircraft flame detonator is prone to causing the nut to loosen due to self-rotation during vibration, posing a safety hazard.
A limiting device is adopted, including a U-shaped block with a screw hole, a round shaft, a threaded rod, and a grooved limiting block. The threaded rod rotates on the inner wall of the U-shaped block with the screw hole, causing the grooved limiting block to be sleeved on the nut, which enhances the limiting at the connection of the locking block. Combined with rubber strips and telescopic rods, it improves friction and stability.
This effectively prevents the locking block from loosening during vibration, improves the safety of the aircraft flare spreader, and reduces the probability of safety hazards.
Smart Images
Figure CN223736245U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of locking bracket technology, and in particular to a locking bracket for fixing a twelve-tube aircraft flame spreader. Background Technology
[0002] The fixing and locking frame is an important component of the aircraft flare dispenser. It is responsible for fixing and locking the flare dispenser to ensure its stability and safety during aircraft flight.
[0003] When the aircraft flare dispenser needs to be installed on an aircraft, the main body of the flare dispenser can be placed inside the inner wall of the first locking block on the fixed mounting bracket. Then, the inner wall of the second locking block is fitted onto the flare dispenser main body opposite the first locking block. Finally, several bolts are passed through the inner walls of both ends of the first and second locking blocks, and then nuts are screwed on to fix the flare dispenser main body on the fixed mounting bracket. Finally, one end of the fixed mounting bracket is fixed to the aircraft with bolts to complete the installation. Since the two ends of the first and second locking blocks are only fixed by bolts and nuts, vibration will occur when the flare dispenser main body is running. Over time, the nuts may rotate and loosen, causing the connection between the first and second locking blocks to loosen. This results in insufficient restraint of the flare dispenser main body, posing a certain safety hazard during use. Utility Model Content
[0004] The purpose of this utility model is to address the shortcomings of existing technologies by proposing a fixing and locking frame for a twelve-tube aircraft flame spreader.
[0005] To achieve the above objectives, this utility model adopts the following technical solution: a fixing and locking frame for a twelve-tube aircraft flare dispenser, comprising a fixing bracket, a second locking block, several bolts, and several nuts. One end of the fixing bracket is fixedly connected to a first locking block. The aircraft flare dispenser body is disposed between the first and second locking blocks. The bolts are inserted into the inner walls of one end of the first and second locking blocks, and one end of the bolts is spirally inserted into the inner wall of the nuts. A locking mechanism is provided between the two ends of the first and second locking blocks. The limiting device includes two U-shaped blocks with screw holes, several L-shaped blocks fixedly connected to the outer surface of the nut, and protrusions symmetrically fixedly connected to one side of both ends of the first locking block. A round shaft is threaded through one end of the U-shaped block with screw holes, and the two ends of the round shaft are threaded through and connected to the two protrusions. A threaded rod is threadedly connected to the inner wall of one end of the U-shaped block with screw holes, and a grooved limiting block is rotatably connected to one end of the threaded rod. One end of the L-shaped block is inserted into the inner wall of the grooved limiting block.
[0006] The effect achieved by the above components is as follows: By setting a limiting device, the U-shaped block with the screw hole can be rotated to a certain position on the protrusion via a round shaft, and then the threaded rod can be rotated in the inner wall of the U-shaped block with the screw hole, causing the inner wall of the groove limiting block to be sleeved on the outer surface of one end of the corresponding L-shaped block. In this way, the groove limiting block can be fixed on the nut, so that the U-shaped block with the screw hole is limited, and the connection between the first locking block and the second locking block is reinforced and limited for a second time. At the same time, the nut is limited so that it is not easy for it to rotate and loosen on the outer surface of the bolt. This can prevent the first locking block and the second locking block from loosening due to vibration of the aircraft flame spreader body during operation, improve the safety during use, and reduce the probability of potential safety hazards.
[0007] Preferably, the inner wall of the groove limiting block is fixedly connected with a plurality of rubber strips, and the plurality of rubber strips are arranged at equal intervals.
[0008] The effect achieved by the above components is that by setting the rubber strip, the contact friction of the inner wall of the groove limiting block can be increased, so that the L-shaped block is not easy to wobble after it is inserted into the inner wall of the groove limiting block, and the nut is more firmly limited.
[0009] Preferably, a telescopic rod is symmetrically fixedly connected to one side of the groove limiting block, and one end of the telescopic rod is fixedly connected to one side of the screw hole U-shaped block.
[0010] The effect achieved by the above components is that by setting the telescopic rod, the movement direction of the groove limiting block can be limited and fixed, making it less likely to rotate with the rotation of the threaded rod, and making it convenient for the groove limiting block to be fitted onto the L-shaped block.
[0011] Preferably, a plurality of screw blocks are fixedly connected to the outer surface of one end of the bolt, and the screw blocks are disposed on the end of the threaded rod away from the groove limiting block.
[0012] The effect achieved by the above components is that by setting the screw block, the contact area at one end of the threaded rod can be increased, making it easier to manually hold and screw it.
[0013] Preferably, bearings are fixedly connected to the outer surfaces of both ends of the circular shaft, and the outer ring of the bearing is fixedly connected to one side of the protrusion.
[0014] The effect achieved by the above components is that by setting bearings, the contact wear between the round shaft and the cam can be reduced, thereby increasing the service life of both.
[0015] Preferably, the adjusting device includes several locking blocks, and a sliding groove is provided on both sides of one end of the fixed mounting bracket. A circular hole is provided on both sides of the inner wall of the sliding groove. A mounting hole frame is slidably connected to the inner wall of the sliding groove. A plurality of circular grooves are provided on both sides of the mounting hole frame. One end of the locking block is inserted into the inner wall of the circular hole and the circular groove. A spring is sleeved on the outer surface of one end of the locking block. The two ends of the spring are fixedly connected to one side of the locking block and the fixed mounting bracket, respectively.
[0016] The effect achieved by the above-mentioned components is as follows: By setting the adjustment device, when the fixed mounting bracket is installed on the aircraft, the locking block can be pulled outward in the round hole to a certain position according to the installation position on the aircraft. This will cause the spring to be stretched and one end of the spring to slide out of the round groove. Then, the mounting bracket can be slid inward or outward in the inner wall of the groove to a certain position to facilitate the installation position on the aircraft. When this is convenient, the locking block can be released. Under the reset action of the spring, one end of the mounting bracket can be locked into the corresponding round groove, fixing and limiting the adjusted mounting bracket. This facilitates the installation of the fixed mounting bracket and improves the adaptability of the fixed mounting bracket.
[0017] Preferably, a pull block is fixedly connected to one side of the card block, and the longitudinal section of the pull block is circular.
[0018] The effect achieved by the above components is that by setting up the pull block, the contact area on one side of the block can be increased, making it easier to manually hold one end and pull it.
[0019] Preferably, anti-slip blocks are symmetrically fixedly connected to one side of the mounting bracket, and the anti-slip blocks are made of rubber.
[0020] The effect achieved by the above components is as follows: by setting anti-slip blocks, the contact friction on one side of the mounting bracket can be increased, making it less likely to slip when it is installed against the aircraft, thus facilitating installation, and at the same time, it is less likely to cause friction with the aircraft and damage to the aircraft body.
[0021] Compared with the prior art, the advantages and positive effects of this utility model are as follows:
[0022] In this invention, by setting a limiting device, the U-shaped block with a screw hole can be rotated to a certain position on the protrusion via a round shaft. Then, the threaded rod rotates in the inner wall of the U-shaped block with a screw hole, causing the inner wall of the groove limiting block to be sleeved on the outer surface of one end of the corresponding L-shaped block. In this way, the groove limiting block can be fixed on the nut, so that the U-shaped block with a screw hole is limited. This provides secondary reinforcement and limiting at the connection between the first locking block and the second locking block. At the same time, it limits the nut so that it is not easy for it to rotate and loosen on the outer surface of the bolt. This can prevent the first locking block and the second locking block from loosening due to vibration of the aircraft flame spreader body during operation, improve the safety during use, and reduce the probability of potential safety hazards. Attached Figure Description
[0023] Figure 1 This is a three-dimensional structural diagram of the present invention;
[0024] Figure 2 This is a three-dimensional structural diagram of the fixed mounting bracket of this utility model;
[0025] Figure 3 for Figure 2 A three-dimensional schematic diagram of the middle section;
[0026] Figure 4 This is a three-dimensional structural diagram of the circular shaft of this utility model.
[0027] Legend: 1. Fixed mounting bracket; 2. Limiting device; 3. Adjusting device; 4. First locking block; 5. Second locking block; 6. Bolt; 7. Nut; 8. Main body of aircraft flame spreader; 21. L-shaped block; 22. Protrusion; 23. Round shaft; 24. Screw hole U-shaped block; 25. Threaded rod; 26. Groove limiting block; 27. Rubber strip; 28. Telescopic rod; 29. Tightening block; 210. Bearing; 31. Slide groove; 32. Round hole; 33. Mounting hole bracket; 34. Round groove; 35. Locking block; 36. Spring; 37. Pulling block; 38. Anti-slip block. Detailed Implementation
[0028] Example 1, such as Figure 1-4As shown, the fixing and locking frame for the twelve-tube aircraft flare dispenser includes a fixing bracket 1, a second locking block 5, several bolts 6, and several nuts 7. One end of the fixing bracket 1 is fixedly connected to a first locking block 4. The aircraft flare dispenser body 8 is positioned between the first locking block 4 and the second locking block 5. Bolts 6 are inserted into the inner walls of one end of the first locking block 4 and the second locking block 5, and one end of the bolt 6 is screwed into the inner wall of the nut 7. A limit device 2 is provided between the two ends of the first locking block 4 and the second locking block 5. One end of the fixing bracket 1... Adjustment devices 3 are provided on both sides. The limiting device 2 includes two screw hole U-shaped blocks 24. Several L-shaped blocks 21 are fixedly connected to the outer surface of the nut 7. Protrusions 22 are symmetrically fixedly connected to one side of both ends of the first locking block 4. A round shaft 23 is threaded through one end of the screw hole U-shaped block 24. The two ends of the round shaft 23 are threaded through and connected to the two protrusions 22. A threaded rod 25 is threadedly connected to the inner wall of one end of the screw hole U-shaped block 24. A groove limiting block 26 is rotatably connected to one end of the threaded rod 25. One end of the L-shaped block 21 is inserted into the inner wall of the groove limiting block 26. When the aircraft flare dispenser body 8 needs to be installed on an aircraft for use, the aircraft flare dispenser body 8 can be placed in the inner wall of the first locking block 4 on the fixed mounting bracket 1. Then, the inner wall of the second locking block 5 is fitted onto the aircraft flare dispenser body 8 at the position opposite to the first locking block 4. Finally, several bolts 6 are inserted into the inner walls at both ends from one side of the first locking block 4 toward the second locking block 5, and then tightened with nuts 7. At this time, after the U-shaped block 24 with screw holes is rotated to a certain position on the two protrusions 22 through the round shaft 23, its other end is brought close to one end of the second locking block 5. After the threaded rod 25 is rotated to a certain position in the inner wall of the U-shaped block 24 with screw holes, its groove is limited. The inner wall of the positioning block 26 is fitted onto the outer surface of one end of the L-shaped block 21 on the nut 7. This fixes the groove limiting block 26 onto the nut 7, limiting the U-shaped block 24 of its screw hole. This provides secondary reinforcement and limitation at the connection between the first locking block 4 and the second locking block 5. At the same time, the groove limiting block 26 limits and fixes the L-shaped block 21, making it difficult for the nut 7 to rotate and loosen on the outer surface of the bolt 6. This avoids the first locking block 4 and the second locking block 5 from loosening due to vibration generated during the operation of the aircraft flame spreader body 8, improving safety during use and reducing the probability of potential safety hazards. Finally, one end of the fixed mounting bracket 1 is fixed to the aircraft with bolts 6 to complete the installation.
[0029] Reference Figure 1-4As shown, this embodiment discloses that the inner wall of the groove limiting block 26 is fixedly connected with several rubber strips 27, which are arranged at equal intervals. By setting the rubber strips 27, the contact friction of the inner wall of the groove limiting block 26 can be increased, making it less likely for the L-shaped block 21 to wobble after being inserted into the inner wall of the groove limiting block 26, thus making the nut 7 more securely positioned. A telescopic rod 28 is symmetrically fixedly connected to one side of the groove limiting block 26, and one end of the telescopic rod 28 is fixedly connected to one side of the threaded hole U-shaped block 24. By setting the telescopic rod 28, the movement direction of the groove limiting block 26 can be limited and fixed, making it less likely to rotate with the rotation of the threaded rod 25, and facilitating the groove limiting block 26 to be fitted onto the L-shaped block 21.
[0030] Reference Figure 1-4 As shown in the figure, this embodiment discloses that a plurality of tightening blocks 29 are fixedly connected to the outer surface of one end of the bolt 6. The tightening blocks 29 are disposed on the end of the threaded rod 25 away from the groove limiting block 26. By setting the tightening blocks 29, the contact area of one end of the threaded rod 25 can be increased, making it easier to manually hold and tighten it. Bearings 210 are fixedly connected to the outer surfaces of both ends of the round shaft 23. The outer ring of the bearing 210 is fixedly connected to one side of the protrusion 22. By setting the bearings 210, the contact wear between the round shaft 23 and the protrusion 22 can be reduced, thereby improving the service life of both.
[0031] Reference Figure 1-4 As shown, this embodiment discloses an adjustment device 3 including a plurality of locking blocks 35. A sliding groove 31 is provided on both sides of one end of the fixed mounting bracket 1. A round hole 32 is provided on both sides of the inner wall of the sliding groove 31. A mounting hole bracket 33 is slidably connected to the inner wall of the sliding groove 31. A plurality of round grooves 34 are provided on both sides of the mounting hole bracket 33. One end of the locking block 35 is inserted into the inner wall of the round hole 32 and the round groove 34. A spring 36 is sleeved and connected to the outer surface of one end of the locking block 35. The two ends of the spring 36 are fixedly connected to the locking block 35 and one side of the fixed mounting bracket 1, respectively. When installing the fixed mounting bracket 1 on the aircraft, depending on the installation position on the aircraft, first pull the locking block 35 outward in the circular hole 32 to a certain position, causing the spring 36 to be stretched open and one end of it to slide out of the circular groove 34. Then, slide the mounting hole bracket 33 inward or outward in the inner wall of the sliding groove 31 to a certain position to facilitate adaptation to the installation position on the aircraft. Then, release the locking block 35. Under the reset action of the spring 36, one end of it can be locked into the corresponding circular groove 34, fixing and limiting the adjusted mounting hole bracket 33, which facilitates the installation of the fixed mounting bracket 1 and improves the usability of the fixed mounting bracket 1.
[0032] Reference Figure 1-4As shown, this embodiment discloses a pull block 37 fixedly connected to one side of the locking block 35. The longitudinal section of the pull block 37 is annular. By setting the pull block 37, the contact area on one side of the locking block 35 can be increased, making it easier to manually grasp and pull one end. Anti-slip blocks 38, made of rubber, are symmetrically fixedly connected to one side of the mounting bracket 33. By setting the anti-slip blocks 38, the contact friction on one side of the mounting bracket 33 can be increased, making it less prone to slippage when installed on the aircraft, facilitating installation, and preventing friction with the aircraft that could damage the aircraft body.
[0033] Working principle: When the aircraft flare dispenser body 8 needs to be installed on an aircraft, the aircraft flare dispenser body 8 can be placed in the inner wall of the first locking block 4 on the fixed mounting bracket 1. Then, the inner wall of the second locking block 5 is fitted onto the aircraft flare dispenser body 8 opposite the first locking block 4. Finally, several bolts 6 are inserted into the inner walls at both ends from one side of the first locking block 4 toward the second locking block 5, and then tightened with nuts 7. At this time, after the U-shaped block 24 with screw holes is rotated to a certain position on the two protrusions 22 through the round shaft 23, its other end is brought close to one end of the second locking block 5. After holding the screwing block 29 and rotating the threaded rod 25 in the inner wall of the U-shaped block 24 with screw holes to a certain position, the telescopic rod 28... Under the limiting action, the inner wall of the groove limiting block 26 is sleeved on the outer surface of one end of the L-shaped block 21 on the nut 7. In this way, the groove limiting block 26 can be fixed on the nut 7, and the U-shaped block 24 of the screw hole is limited. The connection between the first locking block 4 and the second locking block 5 is reinforced and limited for a second time. At the same time, the groove limiting block 26 will limit and fix the L-shaped block 21, so that the nut 7 is not easy to rotate and loosen on the outer surface of the bolt 6. This can prevent the first locking block 4 and the second locking block 5 from loosening due to vibration generated during the operation of the aircraft flame spreader body 8, improve the safety during use, and reduce the probability of potential safety hazards. Finally, one end of the fixed mounting bracket 1 is fixed to the aircraft with bolt 6 to complete the installation.
[0034] When installing the fixed mounting bracket 1 on the aircraft, depending on the installation position on the aircraft, first pull the locking block 35 outward in the circular hole 32 to a certain position, causing the spring 36 to be stretched open and one end of it to slide out of the circular groove 34. Then, slide the mounting hole bracket 33 inward or outward in the inner wall of the sliding groove 31 to a certain position to facilitate adaptation to the installation position on the aircraft. Then, release the locking block 35. Under the reset action of the spring 36, one end of it can be locked into the corresponding circular groove 34, fixing and limiting the adjusted mounting hole bracket 33, which facilitates the installation of the fixed mounting bracket 1 and improves the usability of the fixed mounting bracket 1.
Claims
1. A fixed locking frame for a twelve-tube aircraft flame-spreading sower, comprising a fixed mounting frame (1), a second locking block (5), a plurality of bolts (6) and a plurality of nuts (7), characterized in that: One end of the fixed mounting frame (1) is fixedly connected with a first locking block (4), the first locking block (4) and the second locking block (5) are provided with an aircraft flame strip sower body (8), the bolt (6) is inserted into the inner wall of one end of the first locking block (4) and the second locking block (5), one end of the bolt (6) is screwed into the inner wall of the nut (7), the two ends of the first locking block (4) and the second locking block (5) are provided with a limiting device (2), one end of the fixed mounting frame (1) is provided with an adjusting device (3) on both sides, the limiting device (2) comprises two screw hole U-shaped blocks (24), the outer surface of the nut (7) is fixedly connected with a plurality of L-shaped blocks (21), the two ends of the first locking block (4) are fixedly connected with a protruding block (22) on one side, one end of the screw hole U-shaped block (24) is connected with a circular shaft (23), the two ends of the circular shaft (23) are connected with the two protruding blocks (22), the inner wall of one end of the screw hole U-shaped block (24) is threadedly connected with a threaded rod (25), one end of the threaded rod (25) is rotatably connected with a recessed groove limiting block (26), one end of the L-shaped block (21) is inserted into the inner wall of the recessed groove limiting block (26).
2. The twelve tube aircraft ribbon spreader fixed locking rack of claim 1, wherein: The inner wall of the recessed groove limiting block (26) is fixedly connected with a plurality of rubber strips (27), and the plurality of rubber strips (27) are arranged at equal distances.
3. The twelve tube aircraft flare dispenser fixed locking rack of claim 1, wherein: One side of the recessed groove limiting block (26) is fixedly connected with a telescopic rod (28), and one end of the telescopic rod (28) is fixedly connected with one side of the screw hole U-shaped block (24).
4. The twelve tube aircraft flare dispenser fixed locking rack of claim 1, wherein: One end of the bolt (6) is fixedly connected with a plurality of twisting blocks (29), and the twisting blocks (29) are arranged on one end of the threaded rod (25) away from the recessed groove limiting block (26).
5. The twelve tube aircraft flare dispenser fixed locking rack of claim 1, wherein: The outer surfaces of the two ends of the circular shaft (23) are fixedly connected with bearings (210), and the outer rings of the bearings (210) are fixedly connected with one side of the protruding block (22).
6. The twelve-tube aircraft flare dispenser fixed locking rack of claim 1, wherein: The adjusting device (3) comprises a plurality of clamping blocks (35), one end of the fixed mounting frame (1) is provided with a sliding groove (31) on both sides, the inner walls of the sliding grooves (31) are provided with circular holes (32) on both sides, the inner walls of the sliding grooves (31) are slidably connected with mounting hole frames (33), the two sides of the mounting hole frames (33) are provided with a plurality of circular grooves (34), one end of the clamping block (35) is inserted into the inner walls of the circular holes (32) and the circular grooves (34), one end of the clamping block (35) is sleeved with a spring (36), and the two ends of the spring (36) are fixedly connected with the clamping block (35) and one side of the fixed mounting frame (1), respectively.
7. The twelve-tube aircraft flare dispenser fixed locking rack of claim 6, wherein: One side of the clamping block (35) is fixedly connected with a pulling block (37), and the longitudinal section of the pulling block (37) is circular.
8. The twelve-tube aircraft flare dispenser fixed locking rack of claim 6, wherein: One side of the mounting hole frame (33) is fixedly connected with a non-slip block (38), and the non-slip block (38) is made of rubber.