Spin-based stable rocket launching device
By installing rotating components and a primer copper cap inside the rocket, the rocket can spin using the high-temperature and high-pressure gas generated by fuel combustion, thus solving the problem of poor rocket self-stabilization and achieving higher flight stability while reducing manufacturing costs.
Patent Information
- Application Number
- CN202421196838.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-29
- Publication Date
- 2025-01-10
- Estimated Expiration
- 2034-05-29
AI Technical Summary
Existing wingless rocket-guided capture net technology suffers from poor rocket self-stabilization capabilities, and the vector engine has a complex structure and high manufacturing cost, resulting in a low interception success rate.
A spin-based rocket stabilization launch device is adopted. By setting a rotating component and a primer copper cap inside the rocket, the high temperature and high pressure gas generated by fuel combustion makes the rocket spin at high speed, ensuring that the rocket obtains good axis stability during the launch phase.
It improved the rocket's flight stability, reduced manufacturing and operating costs, and increased the launch success rate.
Smart Images
Figure CN222336194U_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the technical field of rocket stabilized launch devices, and specifically to a spin-based rocket stabilized launch device. Background Art
[0002] With the development of related hardware and software, drones have been widely used in various occasions in life, and illegal flights have occurred frequently, affecting public safety. In modern warfare, drones have been used in large quantities and have caused considerable losses. Anti-drone technology has become a popular research direction, and a large number of scientific researchers have gradually shifted their attention to the research of anti-drone equipment.
[0003] Anti-UAV technology mainly consists of non-contact radio interference and contact mechanical strikes. In the contact mode, anti-UAV capture net technology often uses drone dragging, which has a small interception area and a low success rate; and uses rocket-towed capture nets to intercept target drones over a large area. The existing wingless rocket-towed capture net technology has poor rocket self-stabilization ability and mostly uses the adjustment of the external angle of the vector engine nozzle to control the flight attitude of the rocket. The vector engine has a complex structural design, limited deflection angle, and high manufacturing cost.
[0004] Therefore, in order to solve the above problems, it is necessary to provide a rocket stabilization launch device that can stabilize the rocket through spin. Summary of the invention
[0005] The purpose of this application is to provide a spin-based rocket stabilized launch device to solve the above-mentioned technical problems.
[0006] To achieve the above-mentioned purpose, the present application provides the following technical solutions: a spin-based rocket stable launching device, comprising: a launching base and a launching chamber, the launching chamber is a hollow structure, one end of the launching chamber is connected to the launching base, the launching base is provided with an installation chamber, the hollow part of the launching chamber is connected to the installation chamber, a rocket is installed in the launching chamber, a power hole is provided at one end of the rocket close to the installation chamber, a rotating component is installed in the power hole, one end of the rotating component is connected to the power hole, an end of the rotating component away from the power hole is arranged close to a primer copper cap in the installation chamber, a primer copper cap has fuel installed in it, an end of the primer copper cap away from the rotating component is exposed on the outside of the launching base, and a plurality of evenly distributed inclination angles are provided at one end of the rotating component away from the power hole, the inclination angles of the plurality of inclination angles are consistent and the inclination surface is an arc surface.
[0007] When using this spin-based rocket stable launch device, the external firing pin hits the ignition copper cap, the fuel burns to produce a large amount of high-temperature and high-pressure gas, which impacts the rotating component to rotate, and the rotating component drives the rocket to rotate at high speed and launch. Therefore, this application causes the rocket to spin during the launch phase, so that the rocket obtains good axial stability and improves the rocket's flight stability.
[0008] Preferably, one end of the rotating component connected to the power hole is provided with a plurality of connecting blocks, and the corresponding connecting blocks in the power hole of the rocket are provided with a plurality of connecting block holes. The rotating component is slidingly connected to the inner wall of the power hole. When the rotating component is impacted and rotates, the rotating component slides along the inner wall of the power hole so that the connecting block and the connecting block hole correspond, and the rotating component drives the rocket to rotate at high speed and launch.
[0009] Preferably, a second primer copper cap is provided between the power hole and the rotating component of the rocket, and the second primer copper cap contains fuel. When the rotating component is impacted and rotates, the rotating component slides along the inner wall of the power hole so that the connecting block and the connecting block hole correspond. The rotating component drives the rocket to rotate at high speed and launch, and at the same time hits the second primer copper cap so that the fuel inside the rocket burns, generating high-temperature and high-pressure gas, which is ejected to continue to propel the rocket to fly.
[0010] Preferably, a primer copper cap column is provided in the middle of several connecting blocks of the rotating component, and the primer copper cap column is arranged corresponding to the primer copper cap 2. The primer copper cap column of the rotating component hits the primer copper cap 2 to cause the internal fuel of the rocket to burn, generate high-temperature and high-pressure gas and eject it.
[0011] Preferably, a power column is connected in the middle of several evenly distributed inclination angles of the rotating component, and the power column is in contact with the primer copper cap in the launch base. When the external firing pin hits the ignition copper cap, the fuel burns to produce a large amount of high-temperature and high-pressure gas, which impacts the power column of the rotating component, so that the power column drives the rotating component and thus drives the rocket to launch.
[0012] Preferably, a launch base cover is provided at the end of the mounting chamber away from the rocket, and a primer copper cap hole is opened in the middle of the launch base cover. The end of the primer copper cap one away from the rotating component is exposed to the outside of the launch base through the primer copper cap hole. The primer copper cap hole limits the primer copper cap one to facilitate the impact of the external firing pin.
[0013] Preferably, the inner side wall of the primer copper cap hole extends toward the launch base cover for a distance to form a primer copper cap bin, and the primer copper cap one is located in the primer copper cap bin.
[0014] Preferably, the inclination angle of the inclination angle is 30-60°, and the inclination angle is subjected to force rotation after being impacted, so that the rotating component rotates.
[0015] Preferably, two symmetrical jet ports are provided at one end of the rocket away from the installation chamber, and the jet ports are inclined at a certain angle relative to the rocket.
[0016] Compared with the prior art, the beneficial effects of this application are:
[0017] 1. This spin-based rocket stabilization launch device can make the rocket spin at high speed during the launch phase, so that the rocket can obtain good axis stability and improve the flight stability of the rocket;
[0018] 2. The spin-based rocket stabilized launch device has a simple structure, low manufacturing difficulty, low assembly and maintenance costs, and is easy and convenient to operate, thereby reducing launch costs and increasing launch success rates. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] Figure 1 This is a schematic diagram of the three-dimensional structure of a spin-based rocket stabilization launch device according to the first embodiment of the present application from one angle;
[0020] Figure 2 This is a schematic structural diagram of the spin-based rocket stabilization launch device without a launch base cover according to the first embodiment of the application;
[0021] Figure 3 This is a schematic cross-sectional structural diagram of a spin-based rocket stabilization launch device according to the first embodiment of the application;
[0022] Figure 4 A schematic diagram of the structure of a power hole of a rocket of a spin-based rocket stabilization launch device according to the first embodiment of the application;
[0023] Figure 5 This is a schematic diagram of a three-dimensional structure of a rotating component of a spin-based rocket stabilization launch device according to the first embodiment of the present application;
[0024] Figure 6 This is a schematic diagram of the matching structure of the rotating component and the primer copper cap 2 of the spin-based rocket stable launch device according to the first embodiment of the present application;
[0025] Figure 7 This is a schematic diagram of the three-dimensional structure of the rotating component of the spin-based rocket stable launch device according to the first embodiment of the present application from another angle;
[0026] Figure 8 This is a schematic cross-sectional structural diagram of the rotating component of the spin-based rocket stabilization launch device and the rocket after installation in Example 1 of the present application;
[0027] Fig. 9 This is a schematic cross-sectional structural diagram of a rocket of the spin-based rocket stabilization launch device according to the first embodiment of the present application;
[0028] Fig.10 This is a schematic diagram of the three-dimensional structure of the spin-based rocket stabilization launch device according to the first embodiment of the present application from another angle;
[0029] Fig.11 This is a schematic diagram of the three-dimensional structure of the spin-based rocket stabilized launch device of Example 2 of the present application.
[0030] Figure numerals: 1. rocket; 11. power hole; 12. jet nozzle; 2. launch chamber; 3. launch base; 31. launch base cover; 311. primer copper cap hole; 4. external firing pin; 5. primer copper cap two; 6. rotating component; 61. connecting block; 62. inclination angle; 63. power column; 64. primer copper cap column; 7. primer copper cap one; 8. ignition copper cap; 9. external firing pin. DETAILED DESCRIPTION
[0031] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.
[0032] Embodiment 1
[0033] like Figures 1 to 10 As shown, a rocket-stabilized launch device based on spin, such as Figure 1 As shown, it includes: a launching base 3 and a launching chamber 2, such as Figure 3 As shown, the launch chamber 2 is a hollow structure, one end of the launch chamber 2 is connected to the launch base 3, the launch base 3 is provided with an installation chamber 32, the hollow part of the launch chamber 2 is connected to the installation chamber 32, and the launch chamber 2 has a built-in rocket 1, as shown in FIG. Figure 2 and 4 As shown, a power hole 11 is provided at one end of the rocket 1 close to the installation chamber 32, and a rotating member 6 is built in the power hole 11. Figures 5 to 7 As shown, the end of the rotating member 6 away from the power hole 11 is provided with four evenly distributed inclination angles 62, the inclination angles of the four inclination angles 62 are all 45°, and the inclination surface is an arc surface, the end of the rotating member 6 connected to the power hole 11 is provided with four connecting blocks 61, and the power hole 11 of the rocket 1 is provided with four connecting block holes corresponding to the connecting blocks 61, and the rotating member 6 is slidably connected to the inner wall of the power hole 11, as shown in FIG. Figure 8 and 9 As shown, a primer copper cap 2 5 is provided between the power hole 11 of the rocket 1 and the rotating member 6, and the primer copper cap 2 5 has fuel inside. A primer copper cap column 64 is provided in the middle of the four connecting blocks 61 of the rotating member 6, and the primer copper cap column 64 is arranged corresponding to the primer copper cap 2 5. A power column 63 is connected in the middle of the four evenly distributed inclinations 62 of the rotating member 6, and the power column 63 contacts the primer copper cap 7 in the launch base 3, as shown in FIG. Fig.10As shown, a launch base cover 31 is provided at the end of the mounting chamber 32 away from the rocket 1, a primer copper cap hole 311 is opened in the middle of the launch base cover 31, and the end of the primer copper cap 7 away from the rotating component 6 is exposed outside the launch base 3 through the primer copper cap hole 311, and the inner wall of the primer copper cap hole 311 extends toward the launch base cover 31 for a distance to form a primer copper cap chamber, and the primer copper cap 7 is located in the primer copper cap chamber, and the primer copper cap 7 has fuel built in it.
[0034] In summary, if Figure 3 As shown, when the external firing pin 4 hits the primer copper cap 17, the fuel in the primer copper cap 17 burns to produce a large amount of high-temperature and high-pressure gas, which impacts the rotating member 6 to rotate and makes the rotating member 6 slide into the power hole 11 of the rocket body 1. At this time, the connecting block 61 enters the connecting block hole, and the rotating member 6 drives the rocket 1 to rotate at high speed and launch. The rotating member 6 further hits the primer copper cap 25, so that the fuel in the primer copper cap 25 burns to produce high-temperature and high-pressure gas, which is ejected and continues to push the rocket 1 to fly. The rocket stable launch device based on spin has a simple structural design and low manufacturing cost. The rocket can be made to spin during the launch phase, so that the rocket has good axial stability and improves the flight stability of the rocket.
[0035] Embodiment 2
[0036] like Fig.11 As shown, a spin-based rocket stable launching device is shown. The difference between this embodiment and the first embodiment is that two symmetrical jet nozzles 12 are opened at one end of the rocket 1 away from the installation chamber 32, and the jet nozzles 12 are inclined at a certain angle relative to the rocket 1. On the basis of the first embodiment, the fuel in the primer copper cap 2 5 burns to produce high-temperature and high-pressure gas, and the gas is ejected to continue to push the rocket 1 to fly. At this time, the gas is ejected from the two angled jet nozzles 12 at the head of the rocket to push the rocket forward, and spin is generated through this angle, making the rocket flight more stable.
[0037] It is obvious to those skilled in the art that the present application is not limited to the details of the exemplary embodiments described above, and that the present application can be implemented in other specific forms without departing from the spirit or essential features of the present application. Therefore, the embodiments should be regarded as exemplary and non-limiting in all respects, and the scope of the present application is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims be included in the present application. Any reference numeral in a claim should not be regarded as limiting the claim to which it relates.
Claims
1. A rocket-stabilized launch device based on spin, characterized in that: include: A launching base (3) and a launching chamber (2), wherein the launching chamber (2) is a hollow structure, one end of the launching chamber (2) is connected to the launching base (3), the launching base (3) is provided with an installation chamber (32), the hollow part of the launching chamber (2) is communicated with the installation chamber (32), the launching chamber (2) has a rocket (1) built in, the end of the rocket (1) close to the installation chamber (32) is provided with a power hole (11), the power hole (11) has a rotating component (6) built in, one end of the rotating component (6) is connected to the power hole (11), the end of the rotating component (6) away from the power hole (11) is arranged close to a primer copper cap (7) in the installation chamber (32), the primer copper cap (7) has fuel built in, the end of the primer copper cap (7) away from the rotating component (6) is exposed outside the launching base (3), the end of the rotating component (6) away from the power hole (11) is provided with a plurality of evenly distributed inclination angles (62), the inclination angles of the plurality of inclination angles (62) are consistent and the inclination surface is an arc surface.
2. A spin-based rocket stabilization launch device according to claim 1, characterized in that: One end of the rotating component (6) connected to the power hole (11) is provided with a plurality of connection blocks (61); a plurality of connection block holes are provided in the power hole (11) of the rocket (1) corresponding to the connection blocks (61); and the rotating component (6) is slidably connected to the inner wall of the power hole (11).
3. A spin-based rocket stabilization launch device according to claim 1 or 2, characterized in that: A second primer copper cap (5) is provided between the power hole (11) of the rocket (1) and the rotating component (6), and the second primer copper cap (5) contains fuel.
4. A spin-based rocket stabilization launch device according to claim 3, characterized in that: A primer copper cap column (64) is provided in the middle of a plurality of connecting blocks (61) of the rotating component (6), and the primer copper cap column (64) is arranged corresponding to the primer copper cap 2 (5).
5. A spin-based rocket stabilization launch device according to claim 1, characterized in that: A power column (63) is connected between a plurality of evenly distributed inclination angles (62) of the rotating component (6), and the power column (63) is in contact with a primer copper cap (7) in the launching base (3).
6. A spin-based rocket stabilization launch device according to claim 1, characterized in that: A launch base cover (31) is provided at one end of the installation chamber (32) away from the rocket (1), a primer copper cap hole (311) is provided in the middle of the launch base cover (31), and an end of the primer copper cap (7) away from the rotating member (6) is exposed outside the launch base (3) through the primer copper cap hole (311).
7. A spin-based rocket stabilization launch device according to claim 6, characterized in that: The inner side wall of the primer copper cap hole (311) extends a distance toward the launch base cover (31) to form a primer copper cap bin, and the primer copper cap one (7) is located in the primer copper cap bin.
8. A spin-based rocket stabilization launch device according to claim 1, characterized in that: The inclination angle of the inclination angle (62) is 30-60°.
9. A spin-based rocket stabilization launch device according to claim 1, characterized in that: Two symmetrical jet ports (12) are provided at one end of the rocket (1) away from the installation chamber (32), and the jet ports (12) are inclined at a certain angle relative to the rocket (1).