Small cruise target projectile modified based on retired equipment
By restructuring and decommissioned anti-tank missiles, small cruise target bombs have been formed, which solves the problems of long development cycle and high cost of existing target bombs, and achieves low-cost, convenient launch and multi-target simulation target bomb training effects.
Patent Information
- Application Number
- CN202510418648.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-03
- Publication Date
- 2025-06-20
AI Technical Summary
The development cycle of existing target missiles is long and costly. The technology of using active or retired missiles to renovate target missiles is moderate but costly. The flight trajectory of target missiles modified with retired rockets is far from the real combat targets, and cannot meet the extensive and large-scale needs of military training.
The retired anti-tank missile is used as the basis, and the target missile is formed by restructuring its navigation compartment, control compartment and other components, and the target missile's on-board control components and infrared radiation sources are used, combined with the satellite navigation system and on-board flight control system, the target missile's autonomous cruise function is realized.
It significantly reduces the manufacturing cost of target bombs, realizes the miniaturization and convenient launch of target bombs, and can simulate multiple low-altitude subsonic targets, meeting the needs of military training.
Smart Images
Figure CN120176496A_ABST
Abstract
Description
Technical Field
[0001] This application relates to the technical field of cruise target missile manufacturing, and in particular to a small cruise target missile refitted from retired equipment. Background Art
[0002] With the continuous in-depth development of actual combat training in recent years, the training requirements of the troops have become more difficult and strict. The demand for various types of targets has increased significantly and has increasingly become an indispensable key part of future air defense weapon training. At the same time, various military industrial enterprises also need to use targets to verify and test new missiles and air defense systems. Currently, the commonly used targets in China are divided into two categories: target aircraft and target missiles. The target missile has the advantages of high speed and low cost compared with the target aircraft and has gradually become the main force of troops training. At present, there are generally three methods for developing target missiles at home and abroad: specially developing target missiles, refitting using existing or retired missiles, and refitting using retired rockets, but all of them have deficiencies.
[0003] Defects and deficiencies of the prior art: 1. The development cycle of newly developed target missile products is long. The special functional requirements such as high reliability, high precision, and high safety for target supply exceed the technical standards of conventional missiles and targets, with extremely high engineering difficulty and high input costs. 2. Most of the existing target missile refitting schemes using retired / active missiles are to remove redundant components of existing cruise missiles and additionally install equipment such as infrared light sources. This scheme has moderate technical difficulty, but the number of domestic cruise missiles is limited and the cost is high, resulting in its inability to meet the extensive and large-scale requirements of range test identification and troop combat training. 3. The technical difficulty of refitting target missile products using retired rockets is small and the input cost is small, but most of them are uncontrolled flight products, and there is a certain gap between the flight trajectory and the real combat target. Summary of the Invention
[0004] In order to meet the training needs of the troops, reduce the manufacturing cost, and increase the production scale of target missiles, this application provides a small cruise target missile refitted from retired equipment.
[0005] The small cruise target missile refitted from retired equipment provided by this application adopts the following technical solutions: A small cruise target missile based on the refitting of retired equipment, including a retired anti-tank missile. The retired anti-tank missile includes a navigation compartment, an engine, an infrared radiation source, and a control compartment. The navigation compartment includes an antenna assembly, an inner positioning cone threadedly connected to the antenna assembly, an anti-stabilizing fin fixedly connected to the outside of the inner positioning cone, a wind cap outer cover connected to the inner positioning cone, a sand-filled projectile body connected to the wind cap outer cover, a guidance compartment arranged inside the sand-filled projectile body, a battery connected to the guidance compartment, and an aviation plug connected to the end of the sand-filled projectile body. The control compartment uses the on-board control components of the retired anti-tank missile. Gyro signals and high-voltage signals are sent to the control compartment, and control instructions are sent from the navigation compartment to the control compartment.
[0006] By adopting the above technical solutions, the control compartment of the present application uses the on-board control components of the retired anti-tank missile to refit the retired anti-tank missile, reducing the manufacturing cost. By adding a navigation compartment, the present application becomes a cruise target missile. The navigation compartment replaces the warhead of the retired anti-tank missile. The guidance compartment and battery arranged in the navigation compartment form a satellite navigation system, an on-board flight control system, an on-board battery system, etc. The sand-filled projectile body is used for weight balancing, so that the shape and aerodynamic characteristics of the navigation compartment are exactly the same as those of the warhead of the retired anti-tank missile. The control compartment and the navigation compartment are electrically connected, and the on-board control components of the retired anti-tank missile are used as the signal connection path between the navigation compartment and the control box, reducing the manufacturing cost of the cruise target missile, meeting the training needs of the troops, and achieving the purpose of troops training.
[0007] Optionally, the antenna assembly includes an antenna outer cover, an antenna, and a simulation probe. The simulation probe is threadedly connected to the inner positioning cone, and the antenna head cover is fixedly connected to the simulation probe.
[0008] By adopting the above technical solutions, the basic purpose of signal transmission of the antenna assembly is achieved.
[0009] Optionally, the antenna model is HX-SCPD024, the antenna outer cover is a non-metallic material nylon rod antenna outer cover, the simulation probe is a non-metallic material nylon rod simulation probe, the thickness of the antenna head cover is two millimeters, and the antenna head cover and the simulation probe are fixed by epoxy glue.
[0010] By adopting the above technical solutions, the performance of the antenna assembly is improved.
[0011] Optionally, the guidance compartment includes a housing, a head housing connected to the housing, a combined navigation module connected to the housing, and a bottom cover. The combined navigation module includes a flight control component and a navigation module. The flight control component is connected to the head housing, the navigation module is connected to the housing, batteries are connected to the side wall of the head housing and the top of the housing, and a base is threadedly connected to the navigation module.
[0012] By adopting the above technical solution, the purpose of the guidance cabin of the present application is achieved, and the training requirements of the troops for target missiles are met.
[0013] Optionally, the infrared radiation source is a retired anti-tank missile radiation source, which is fixedly connected to the outer wall of the engine. The infrared radiation source includes a housing, a plastic plug, and a wind cap. The housing is filled with a combustion agent, and the plastic plug is filled with an electric ignition tube and a wire.
[0014] By adopting the above technical solution, the utilization rate of the components of the retired anti-tank missile is achieved, and the infrared characteristics of the target missile are provided.
[0015] Optionally, the plug of the engine is a three-core plug.
[0016] Optionally, the anti-stabilizing fin, the inner positioning cone, and the wind cap outer cover all adopt the original structure of the retired anti-tank missile.
[0017] By adopting the above technical solution, the utilization rate of the components of the retired anti-tank missile is achieved, the manufacturing cost of the cruise target missile is reduced, and the training requirements of the troops are met.
[0018] In summary, the present application includes at least one of the following beneficial technical effects: The present application uses a retired anti-tank missile to develop a cruise target missile, and at the same time maximally utilizes the original missile components, significantly reducing the manufacturing cost; Compared with the traditional cruise target missile product, the volume of this type of target missile product is significantly reduced, and the launch is more convenient; Through the satellite navigation deviation measurement and correction solution, the present application realizes the autonomous cruise function of the target missile and can simulate various types of low-altitude subsonic targets. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] Figure 1 is a schematic structural diagram of a small cruise target missile based on the reform of retired equipment disclosed in the embodiment of the present application.
[0020] Figure 2 is a schematic diagram of the navigation cabin in the embodiment of the present application.
[0021] Figure 3 is a schematic diagram of the antenna assembly in the embodiment of the present application.
[0022] Figure 4 is a schematic diagram of the antenna hood in the embodiment of the present application.
[0023] Figure 5 is a schematic diagram of the guidance cabin in the embodiment of the present application.
[0024] Figure 6 is a schematic diagram of the outer shell in the embodiment of the present application.
[0025] Figure 7 It is a schematic diagram of the head housing in the embodiment of the present application.
[0026] Figure 8 It is a schematic diagram of the bottom cover in the embodiment of the present application.
[0027] Figure 9 It is a schematic diagram of the engine socket housing in the embodiment of the present application.
[0028] Figure 10 It is a schematic diagram of the sand-filled projectile body in the embodiment of the present application.
[0029] Figure 11 It is the circuit diagram on the projectile after modification in the embodiment of the present application.
[0030] Explanation of reference numerals: 1. Navigation cabin; 2. Engine; 3. Infrared radiation source; 4. Control cabin; 5. Antenna assembly; 6. Inner positioning cone; 7. Anti-stabilizing fin; 8. Wind cap outer cover; 9. Sand-filled projectile body; 10. Guidance cabin; 11. Battery; 12. Aviation plug; 13. Antenna outer cover; 14. Antenna; 15. Simulation probe; 16. Outer shell; 17. Head housing; 18. Integrated navigation module; 19. Bottom cover. Detailed implementation manners
[0031] The following will Figure 1 - will Figure 11 further elaborate on the present application in conjunction with the attached
[0032] Currently, in order to meet the training requirements of the troops, reduce the manufacturing cost, and increase the production scale of target projectiles, the embodiment of the present application proposes a small cruise target projectile based on the modification of retired equipment.
[0033] The embodiment of the present application discloses a small cruise target projectile based on the modification of retired equipment. Refer to Figure 1 and Figure 2, a small cruise target missile based on the refitting of retired equipment, with a missile length of 1035 mm and a wingspan of 393 mm, including a retired anti-tank missile. The retired anti-tank missile includes a navigation compartment 1, an engine 2, an infrared radiation source 3, and a control compartment 4. The navigation compartment 1 is designed according to the shape of the warhead of the retired anti-tank missile, and the navigation compartment 1 is used to replace the warhead of the retired anti-tank missile. The navigation compartment 1 includes an antenna assembly 5, an inner positioning cone 6 threadedly connected to the antenna assembly 5, an anti-stabilizing fin 7 fixedly connected to the outside of the inner positioning cone 6, a wind cap outer cover 8 connected to the inner positioning cone 6, a sand-filled projectile body 9 connected to the wind cap outer cover 8, a guidance compartment 10 arranged inside the sand-filled projectile body 9, a battery 11 connected to the guidance compartment 10, and an aviation plug 12 connected to the end of the sand-filled projectile body 9. The control compartment 4 utilizes the on-board control components of the retired anti-tank missile. Gyro signals and high-voltage signals are sent to the control compartment 4, and control instructions are sent from the navigation compartment 1 to the control compartment 4.
[0034] The control compartment 4 of this application adopts the on-board control components of the retired anti-tank missile to refit the retired anti-tank missile. Under the principle of not changing the overall external shape structure of the original missile and not affecting the aerodynamic characteristics and power system of the missile system, the manufacturing cost is reduced. At the same time, by adding a navigation compartment 1 and modifying the on-board circuit, this application becomes a cruise target missile. The navigation compartment 1 replaces the warhead of the retired anti-tank missile. The guidance compartment 10 and battery 11 arranged in the navigation compartment 1 form a satellite navigation system, an on-board flight control system, an on-board battery 11 system, etc. Weight is added through the sand-filled projectile body 9, so that the shape and aerodynamic characteristics of the navigation compartment 1 are exactly the same as those of the warhead of the retired anti-tank missile. The control compartment 4 and the navigation compartment 1 are electrically connected, and the on-board control components of the retired anti-tank missile are used as the signal connection path between the navigation compartment and the control box, reducing the manufacturing cost of the cruise target missile, meeting the training needs of the troops, and achieving the purpose of troops training.
[0035] Refer to Figures 3 - 4, the antenna assembly 5 achieves the basic purpose of transmitting signals by the antenna assembly 5. The antenna assembly 5 includes an antenna cover 13, an antenna 14, and an analog probe 15. The head cover of the antenna 14 is fixedly connected to the analog probe 15. The model of the antenna 14 is HX-SCPD024, which is a three-system six-frequency helical antenna 14 covering GPS L1 / L2, GLONASS L1 / L2, and BDS B1 / B2 / B3. It has the advantages of light weight, wide beamwidth of the radiation pattern, and high low-angle gain. It can still receive satellites normally in some occasions with severe occlusion. For example, it can also work normally when the aviation equipment is flying obliquely. The antenna cover 13 is made of non-metallic material nylon rod antenna cover 13, and the analog probe 15 is made of non-metallic material nylon rod analog probe 15, reducing the possibility that the metal material affects the performance of the antenna 14. The overall external dimensions of the head cover of the antenna 14 and the analog probe 15 are the same as the dimensions of the warhead probe of the retired anti-tank missile. The thickness of the head cover of the antenna 14 is 2 mm, minimizing the impact on the performance of the antenna 14. The bottom of the analog probe 15 is machined with a thread of M45×1.5-6g and is connected to the inner positioning cone 6 by means of the thread, achieving the purpose of thread-connecting the analog probe 15 to the inner positioning cone 6. The head cover of the antenna 14 and the analog probe 15 are closely fitted and fixed by epoxy glue, achieving the stable connection between the head cover of the antenna 14 and the analog probe 15.
[0036] Referring to Figures 5 - 8 , the guidance cabin 10 includes a housing 16, a head housing 17 connected to the housing 16, a combined navigation module 18 connected to the housing 16, and a bottom cover 19. The head housing 17, the housing 16, and the bottom cover 19 are all machined from nylon rods, reducing the possibility that the metal material affects the performance of the antenna 14. The combined navigation module 18 includes a flight control component and a navigation module. The flight control component is connected to the head housing 17. A groove is machined on the side of the head housing 17 for fixing the battery 11. The housing 16 is machined according to the shape of the navigation module for fixing and placing the navigation module, achieving the purpose of connecting the navigation module to the housing 16. At the same time, three round holes are opened at the top of the housing 16 for placing the battery 11, achieving the purpose that both the side wall of the head housing 17 and the top of the housing 16 are connected to the battery 11. Four holes are opened on the bottom cover 19, and the flight navigation module is fixed by screws.
[0037] Referring to Figure 9 , the overall structure of the engine 2 is reformed based on the structure of the retired anti-tank missile engine 2. The focus is on reforming the plug of the retired anti-tank missile engine 2. The original two-core plug of the engine 2 is removed and reformed into a three-core plug. At the same time, the socket housing 16 is redesigned, and the BZ-4A military plug is selected for the plug. The socket housing 16 is processed by 3D printing technology.
[0038] The infrared radiation source 3 uses the radiation source of a retired anti-tank missile. The infrared radiation source 3 is fixedly assembled on the outer wall of the engine 2. The infrared radiation source 3 includes a housing, a plastic plug, and a wind cap. The interior of the housing contains a combustion agent, and the interior of the plastic plug contains an electric ignition tube and wires, realizing the utilization rate of the components of the retired anti-tank missile, providing the infrared characteristics of the target missile for training, and achieving the purpose of target missile training.
[0039] Refer to Figure 10 , the sand-filled warhead 9 is processed and weighted based on the shape of the warhead of the original retired anti-tank missile, and based on the housing size of the guidance cabin 10, the internal materials of the sand-filled warhead 9 are removed to facilitate the adjustment of the mass and centroid of the warhead and the placement of the components of the guidance cabin 10. By weighting the sand-filled warhead 9, the shape and aerodynamic characteristics of the navigation cabin 1 and the warhead of the prototype missile are exactly the same. The aviation plug 12 serves as the binding interface for the daily test and launch of the navigation cabin 1.
[0040] The anti-stabilizing fin 7, the inner positioning cone 6, and the wind cap outer cover 8 all use the original warhead structure of the retired anti-tank missile without structural modification. The battery 11 selects a 10650 lithium battery 11.
[0041] Refer to Figure 11 , the control cabin 4 uses the original on-board control components of the anti-tank missile to reform the on-board circuit. The key is to adaptively transform the lead wires of the original gyro and servo, and reform the fuse ignition circuit, which serves as the signal connection path between the navigation cabin 1 and the control cabin 4. The control cabin 4 is reformed based on the control system of the retired anti-tank missile, with the key being the reform of the on-board circuit. During the flight of the missile, the gyro signal and high-voltage signal need to be sent to the control cabin 4, and at the same time, the control command needs to be sent from the navigation cabin 1 to the control cabin 4, so the circuit design needs to be redone. After analysis and demonstration, the original fuse power supply circuit is reformed: the original fuse power supply circuit is removed, and three core wires are led out from points 1, 2, and 6 of the distributor. The on-board circuit after reform is shown in the appendix Figure 11 .
[0042] The implementation principle of a small cruise target missile based on the reform of retired equipment in the embodiment of this application is as follows: This application adopts an overall technical solution of ground launch binding and power supply, on-board program instructions plus satellite navigation deviation measurement and correction. After the target missile is launched, the battery 11 system starts to supply power to the navigation module and flight control module in the navigation cabin 1. The navigation module measures the flight deviation of the missile, and the flight control module generates control instructions to drive the servo to work, and real-time corrects the flight parameters of the target missile, so as to complete the flight of the missile along the independently preset trajectory after launch, achieving the purpose of simulating a low-altitude subsonic target.
[0043] The above are all the preferred embodiments of this application, and this application's protection scope is not limited accordingly. Therefore, all equivalent changes made according to the structure, shape, and principle of this application should be covered within the protection scope of this application.
Claims
1. A small cruise target missile modified from retired equipment, comprising a retired anti-tank missile, wherein the retired anti-tank missile comprises a navigation cabin (1), an engine (2), an infrared radiation source (3) and a control cabin (4), characterized in that: The navigation cabin (1) comprises an antenna assembly (5), an inner positioning cone (6) threadedly connected to the antenna assembly (5), an anti-stabilizing wing surface (7) fixedly connected to the outside of the inner positioning cone (6), a hood cover (8) connected to the inner positioning cone (6), a sand-filled projectile (9) connected to the hood cover (8), a guidance cabin (10) arranged inside the sand-filled projectile (9), a battery (11) connected to the guidance cabin (10), and an aviation plug (12) connected to the end of the sand-filled projectile (9). The control cabin (4) uses the control assembly on the retired anti-tank missile, and the gyro signal and the high-voltage signal are sent to the control cabin (4), and the control command is sent from the navigation cabin (1) to the control cabin (4).
2. According to claim 1, a small cruise target missile modified from retired equipment is characterized in that: The antenna assembly (5) comprises an antenna cover (13), an antenna (14), and a simulated probe rod (15); the simulated probe rod (15) is threadedly connected to the inner positioning cone (6); and the antenna (14) head cover is fixedly connected to the simulated probe rod (15).
3. The small cruise target missile modified from retired equipment according to claim 2 is characterized by: The antenna (14) has a model of HX-SCPD024, the antenna cover (13) is a non-metallic nylon rod antenna cover (13), the simulated probe rod (15) is a non-metallic nylon rod simulated probe rod (15), the antenna (14) head cover has a thickness of two millimeters, and the antenna (14) head cover and the simulated probe rod (15) are fixed by epoxy glue.
4. The small cruise target missile modified from retired equipment according to claim 2 is characterized in that: The guidance cabin (10) comprises an outer shell (16), a head shell (17) connected to the outer shell (16), a combined navigation module (18) connected to the outer shell (16), and a bottom cover (19); the combined navigation module (18) comprises a flight control component and a navigation module; the flight control component is connected to the head shell (17); the navigation module is connected to the outer shell (16); the side wall of the head shell (17) and the top of the outer shell (16) are both connected to batteries (11); and the base is threadedly connected to the navigation module.
5. The small cruise target missile modified from retired equipment according to claim 4 is characterized in that: The infrared radiation source (3) is a retired anti-tank missile radiation source, and the infrared radiation source (3) is fixedly connected to the outer wall of the engine (2). The infrared radiation source (3) comprises a shell, a plastic plug and a wind cap, the shell contains a combustion agent, and the plastic plug contains an electric ignition tube and a wire.
6. The small cruise target missile modified from retired equipment according to claim 1 is characterized by: The plug of the engine (2) is a three-core plug.
7. The small cruise target missile modified from retired equipment according to claim 1 is characterized by: The anti-stabilizing wing surface (7), the inner positioning cone (6), and the wind cap outer cover (8) all use the original structure of the retired anti-tank missile.