Manual adjustment mechanism for caliber of director of weather modification rocket launcher

Abstract

The utility model discloses a manual adjusting mechanism of weather modification rocket launcher director bullet diameter, belongs to weather modification operation equipment technical field. The mechanism includes bearing rail frame, U type fixed track, limiting rod, U type movable track, adjusting mechanism and locking mechanism, through manual operation handle, through the linkage and connecting rod drive U type movable track in its preset limiting gap and slope track movement, to form the launch containment circle suitable for 44mm, 56mm, 66mm and 82mm etc. different bullet diameter rocket projectile, the utility model discloses pure mechanical structure, has saved the complex electric control system, has simple structure, low manufacturing cost, convenient operation, reliable work and so on, realized one machine multiple use, significantly promoted the operation efficiency and economy.

Description

Technical Field

[0001] This utility model relates to the field of equipment technology for artificial weather modification operations, specifically to a launch mechanism for a rocket launcher orienter that allows manual adjustment of the diameter of the orbital containment circle to accommodate rockets of different diameters. Background Technology

[0002] In weather modification operations (such as hail suppression and rain enhancement), rockets of different diameters are typically required. Traditional rocket launchers mostly adopt a single-channel, single-diameter design, meaning that one launch channel can only launch rockets of a specific diameter. When rockets of different diameters need to be launched, multiple launchers of the corresponding diameters must be deployed at the same operation point, which significantly increases equipment costs, storage costs, and operation preparation time.

[0003] Chinese utility model patent CN 211855057 U discloses an adaptive artificial rainmaking and hail suppression rocket launcher and control system. It uses an electric actuator to drive a shaft connecting rod, causing a moving component to move up and down, thereby changing the envelope diameter of a U-shaped small track. Feedback is obtained through a displacement sensor to achieve automatic control. However, its structure is complex, relying on electric actuators, sensors, controllers, and control logic, resulting in high system integration and significant technical implementation challenges. The cost is also high, with numerous non-standard parts, slide rails, and electronic control components leading to high procurement and maintenance costs. Reliability is also a challenge, as the stability and reliability of electronic components are tested in harsh outdoor environments. Utility Model Content

[0004] The purpose of this invention is to provide a manual adjustment mechanism for the diameter of a rocket launcher directional device for artificial weather modification. This adjustment mechanism has the advantages of simple structure, low cost, reliable operation, and multi-diameter adjustment without the need for external power.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: A manual adjustment mechanism for the diameter of a rocket launcher directional device for artificial weather modification includes a rail frame, a U-shaped fixed rail, a limit rod, a U-shaped movable rail, an adjustment mechanism, and a locking mechanism.

[0006] The rail frame is the main support body of the mechanism, and a limiting notch is provided inside it.

[0007] The U-shaped fixed track is fixedly installed inside the rail support frame.

[0008] The limiting rod is fixedly installed inside the rail frame and located on one side of the U-shaped fixed rail.

[0009] The U-shaped movable track is slidably set within the limiting notch of the rail frame by means of a pin; the side of the U-shaped movable track is provided with multiple limiting notches, including multiple spring diameter limiting ports parallel to the mounting plane of the rail frame and a ramp track at a certain angle to the mounting plane of the rail frame.

[0010] The adjustment mechanism includes a handle, a linkage rod, and a connecting rod; the handle is connected to the linkage rod, and the linkage rod is connected to the U-shaped movable tracks in all channels through multiple connecting rods, so that the operating handle can synchronously drive the movement of all U-shaped movable tracks.

[0011] The locking mechanism includes a T-shaped limiting pin and a B-shaped pin; the linkage rod is provided with limiting holes corresponding to each spring diameter. When the U-shaped movable track moves to the target limiting port, the T-shaped limiting pin can be inserted into the corresponding limiting hole of the linkage rod and the limiting hole of the rail frame at the same time, and fixed by the B-shaped pin, thereby locking the entire adjustment mechanism.

[0012] Preferably, the diameter limiting port includes a limiting position for launching 44mm, 56mm, 66mm and 82mm rockets.

[0013] Preferably, the inclination angle of the ramp track is 150°.

[0014] Preferably, two launch channels are arranged within the rail frame, and the adjustment mechanism simultaneously controls the U-shaped movable tracks within the two channels.

[0015] Preferably, the mechanism can be expanded to four or eight channels by repeating or overlapping the adjustment mechanism.

[0016] Compared with the prior art, the present invention has the following beneficial effects: (1) The pure mechanical manual adjustment method completely eliminates expensive and complex electronic components such as electric actuators, displacement sensors, and controllers, greatly reducing manufacturing and maintenance costs.

[0017] (2) With the cooperation of handle, linkage rod and mechanical limit port, the operator can quickly and accurately complete the bullet diameter switching without professional tools or power supply, adapting to the field operation environment and with high reliability.

[0018] (3) One launcher can cover the launch requirements of multiple commonly used missile diameters, reducing the number of equipment configurations, simplifying logistical support, and greatly improving the flexibility and efficiency of artificial weather modification operations.

[0019] (4) The thrust deviation generated during rocket launch can be absorbed and offset by the slight deformation of the track frame, effectively preventing the left and right deflection and up and down movement of the U-shaped moving track, and ensuring the stability and safety of the launch process. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of this utility model.

[0021] Figure 2 This is a schematic diagram of the limiting notch of the U-shaped movable track of this utility model.

[0022] Figure 3 This is a schematic diagram of the limiting hole of the linkage rod of this utility model.

[0023] Figure 4 This is a side view of the present invention.

[0024] The markings in the diagram are: 1. Rail support frame; 2. T-shaped limit pin; 3. B-shaped pin; 4. Handle; 5. U-shaped fixed rail; 6. Limiting rod; 7. U-shaped movable rail; 8. Pin; 9. Linkage rod; 10. Connecting rod; 11. Fixed rod. Detailed Implementation

[0025] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0026] like Figures 1 to 4 As shown in the embodiment, this is a manual adjustment mechanism for the diameter of a rocket launcher directional device for artificial weather modification. Through mechanical linkage and a limiting structure, it realizes stepless (via ramp) and stepped (via limiting port) adjustment of the diameter of the containment circle. It includes a support frame 1, a T-shaped limiting pin 2, a B-shaped pin 3, a handle 4, a U-shaped fixed track 5, a limiting rod 6, a U-shaped movable track 7, a pin 8, a linkage rod 9, a connecting rod 10, and a fixing rod 11.

[0027] The four rail-supporting frames 1 are connected into an integral frame by connecting rods 11, serving as the main support for the adjustment mechanism; the U-shaped fixed track 5 and the limiting rod 6 are fixedly installed inside the rail-supporting frame 1; the U-shaped movable track 7 is installed in the limiting notch of the rail-supporting frame 1 by pins 8. The pins 8 are fixed on both sides with elastic cylindrical pins, ensuring that they can only move within the preset notch of the U-shaped movable track 7. Figure 2 As shown, the preset notches include limiting ports for the launch positions of 44mm, 56mm, 66mm and 82mm rockets, as well as ramp tracks connecting the limiting ports. The angle between the ramp tracks and the mounting plane is 150°.

[0028] The handle 4 is connected to the linkage rod 9, which is connected to the U-shaped movable track 7 in the two launch channels through four connecting rods 10; operating the handle 4 can synchronously drive the two U-shaped movable tracks 7 to move within the preset gap.

[0029] like Figure 3As shown, the linkage rod 9 is provided with limiting holes corresponding to each bullet diameter; after adjustment, the T-type limiting pin 2 is inserted into the limiting hole of the linkage rod and the limiting hole of the rail frame, and then locked with the B-type pin 3 to prevent the mechanism from loosening during firing.

[0030] To adjust the spring diameter from large to small (82mm → 66mm), first remove pin B3 and pull out pin T2. ​​Then pull handle 4 outward, causing linkage rod 9 to move U-shaped movable track 7 via connecting rod 10. Next, pin 8 slides along the inclined track, causing U-shaped movable track 7 to simultaneously generate horizontal and vertical displacement, thereby increasing its distance from the end of U-shaped fixed track 5 and its vertical distance, thus reducing the diameter of the containment circle. Finally, when pin 8 slides into the 66mm limiting hole, the mechanism is in place. Use the micro-motion handle to align the 66mm limiting hole of linkage rod 9 with the support frame hole, insert pin T2 and pin B3, and locking is complete.

[0031] Adjust the spring diameter from small to large (44mm→56mm), remove type B pin 3, and pull out type T-stop pin 2. Push handle 4 inward, and pin 8 slides along "slope 1," reducing the end distance and vertical distance between the U-shaped movable track 7 and the U-shaped fixed track 5, thus increasing the diameter of the containment circle. When pin 8 slides into the "56 limit" opening, the mechanism is in place. Fine-tune the hole position, insert and lock type T-stop pin 2 and type B pin 3.

[0032] When launching 44mm, 56mm, and 66mm rockets, the rocket is constrained by an enclosing circle formed by the U-shaped fixed track 5 and the U-shaped movable track 7. When launching 82mm rockets, the rocket is constrained by an enclosing circle formed by the U-shaped fixed track 5, the U-shaped movable track 7, and the limiting rod 6.

[0033] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A manual adjustment mechanism for the diameter of a launcher-type projectile on a weather modification rocket, characterized in that, include: The rail frame (1) serves as a support structure and has a limiting notch inside; The U-shaped fixed track (5) is fixedly installed inside the rail frame (1); The limiting rod (6) is fixedly installed inside the rail frame (1); The U-shaped movable track (7) is slidably set in the limiting notch of the rail frame (1) by means of a pin (8); the side of the U-shaped movable track (7) is provided with a plurality of preset notches, the preset notches including parallel spring diameter limiting ports and inclined ramp tracks. The adjustment mechanism includes a handle (4), a linkage rod (9), and a connecting rod (10); the handle (4) is connected to the linkage rod (9), and the linkage rod (9) is connected to the U-shaped movable track (7) through multiple connecting rods (10) to synchronously drive all U-shaped movable tracks (7) to move within the preset notch; The locking mechanism includes a T-type limiting pin (2) and a B-type pin (3); the linkage rod (9) is provided with limiting holes corresponding to each bullet diameter. When the U-shaped movable track (7) moves to the target bullet diameter limiting port, the T-type limiting pin (2) can be inserted into the corresponding limiting hole of the linkage rod (9) and the limiting hole of the rail frame (1) at the same time, and fixed by the B-type pin (3).

2. The manually adjustable mechanism for the range of the director of the weather modification rocket launcher according to claim 1, characterized in that: The diameter limiting port includes a limiting port for defining the launch position of 44mm, 56mm, 66mm and 82mm rockets.

3. The manual range adjustment mechanism of a weather modification rocket launcher director according to claim 1 or 2, characterized in that: The angle between the inclined track and the mounting plane of the rail frame (1) is 150°.

4. The manual adjustment mechanism for the diameter of the launcher of a weather modification rocket as described in claim 1, characterized in that: At least two launch channels are arranged inside the rail frame (1), and the adjustment mechanism simultaneously controls the U-shaped movable rails (7) in all channels.

5. The manual adjustment mechanism for the diameter of the launcher of a weather modification rocket as described in claim 1, characterized in that: When launching rockets with diameters of 44mm, 56mm and 66mm, the rockets are constrained by the U-shaped fixed track (5) and the U-shaped movable track (7); when launching rockets with a diameter of 82mm, the rockets are constrained by the U-shaped fixed track (5), the U-shaped movable track (7) and the limiting rod (6).

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