Multi-purpose high-speed target projectile modified based on retired equipment

Abstract

The invention relates to the technical field of target projectiles, in particular to a multipurpose high-speed target projectile modified based on retired equipment, which comprises a retired rocket projectile shell, a simulated infrared characteristic module, a connecting screw and an RCS characteristic simulation module, the retired rocket projectile shell comprises a simulated combat cabin, a front engine, a rear engine, a projectile tail stabilizing mechanism and a spray pipe, the simulated warhead cabin is located at the front end of the retired rocket projectile shell, the end of the simulated warhead cabin is arranged to be a wave-transparent head cover, the connecting screw piece is located at the middle end of the simulated warhead cabin, the wave-transparent head cover is connected to the connecting screw piece, and the simulated infrared characteristic module and the RCS characteristic simulation module are both in threaded connection with the connecting screw piece. The infrared characteristic simulation module and the RCS characteristic simulation module are located at the two ends of the connecting screw piece respectively, the infrared characteristic simulation module comprises an illumination torch located in the simulated combat cabin, and the RCS characteristic simulation module comprises a Luneberg ball base and a Luneberg ball. The method has the advantage of being convenient for troop training.

Description

Technical Field

[0001] This application relates to the technical field of target missiles, and in particular to a multi-purpose high-speed target missile modified based on retired equipment. Background Art

[0002] In recent years, with the rapid development of unmanned aircraft such as unmanned aerial vehicles and cruise missiles, modern warfare mainly relies on air raids and long-range strikes as the main offensive means. Most of these aircraft have subsonic and transonic flight characteristics, are difficult to capture, and have a large lethality. This has put higher and higher requirements on the air defense and anti-missile combat capabilities of the troops. However, due to factors such as cost and training methods, medium and low-speed target drones are still commonly used for live ammunition shooting in actual combat training of the troops, which is quite different from actual combat. In this context, target missile products with lower cost and higher speed have emerged. Currently, there are generally three methods for developing target missiles at home and abroad: specially developing target missiles, modifying using active or retired missiles, and modifying using active or retired rockets. Target missile products modified using active or retired rockets have higher cost advantages and can meet the growing training needs of the troops. In recent years, the related technologies have developed rapidly.

[0003] However, there are still some deficiencies in the related products on the market at present. First, due to the relatively small infrared and radar characteristics of the rocket itself, additional infrared light sources or RCS characteristic devices need to be added to improve the corresponding characteristics. Most products can only add one type of device, resulting in a single simulated target and being unable to simultaneously simulate infrared and radar characteristics. Second, most rocket target missile products are small in size, fast in flight speed, and difficult to visually capture after launch. Especially for radar characteristic target missile products, it brings inconvenience to the training of the troops. Summary of the Invention

[0004] In order to facilitate the training of the troops, this application provides a multi-purpose high-speed target missile modified based on retired equipment.

[0005] The multi-purpose high-speed target missile modified based on retired equipment provided by this application adopts the following technical solutions: A multi-purpose high-speed target missile based on the refitting of retired equipment, comprising a retired rocket shell, an infrared characteristic simulation module, connecting screws, and an RCS characteristic simulation module. The retired rocket shell includes a simulated combat cabin, a front engine connected to the simulated combat cabin, a rear engine, a tail stabilizer mechanism, and a nozzle. The simulated combat cabin is located at the front end of the retired rocket shell, and the end of the simulated combat cabin is provided with a radar-transparent nose cone. The front engine is located between the rear engine and the simulated combat cabin, and the rear engine is located between the front engine and the tail stabilizer mechanism. The infrared characteristic simulation module, the connecting screws, and the RCS characteristic simulation module are all connected to the inside of the simulated combat cabin. The connecting screws are located in the middle of the simulated combat cabin. The radar-transparent nose cone is connected to the connecting screws. The infrared characteristic simulation module and the RCS characteristic simulation module are both threadedly connected to the connecting screws. The infrared characteristic simulation module and the RCS characteristic simulation module are respectively located at both ends of the connecting screws. The infrared characteristic simulation module includes a flare located inside the simulated combat cabin. The RCS characteristic simulation module includes a Luneburg sphere base provided inside the simulated combat cabin and a Luneburg sphere connected to the Luneburg sphere base.

[0006] By adopting the above technical solution, the simulated combat cabin provides an installation position for other components. The front engine and the rear engine provide power for the target missile to achieve the basic training purpose of the target missile. The infrared characteristic simulation module and the RCS characteristic simulation module are installed inside the retired rocket shell, which can simultaneously simulate infrared characteristic targets and RCS characteristic targets, meeting the training requirements of the troops and facilitating the training of the troops.

[0007] Optionally, the infrared characteristic simulation module further includes a base connected to the inner wall of the simulated combat cabin, a connecting cover detachably connected to the base, an ignition cartridge detachably connected to the base, and an automatic igniter threadedly connected to the connecting screw. The base is threadedly connected to the front engine. The flare is threadedly connected to the base. The flare and the front engine are respectively located at both ends of the base. The end of the flare away from the base is threadedly connected to the connecting screw. The connecting cover is threadedly connected to the base. The connecting cover covers the flare. The ignition cartridge is fixedly connected to the base by screws. The ignition cartridge presses against the flare. The automatic igniter is threadedly connected to the surface of the connecting screw facing the base. The automatic igniter is electrically connected to the ignition cartridge.

[0008] By adopting the above technical solution, the base provides an installation position for the connection cover. During daily duty, a short circuit occurs between the automatic ignition component and the ignition cartridge. When in use, the automatic ignition component is connected to the ignition cartridge through a plug. Before the target missile is launched, the automatic ignition component is connected to the ignition cartridge. After launch, it is activated by the launch overload to supply power to the ignition cartridge. After the ignition cartridge works, it ignites the illumination torch to achieve the purpose of simulating an infrared characteristic target.

[0009] Optionally, a plurality of rectangular holes are formed in the side wall of the connection cover.

[0010] By adopting the above technical solution, the rectangular holes serve as the radiation windows of the illumination torch to achieve the purpose of simulating an infrared characteristic target.

[0011] Optionally, the RCS characteristic simulation module further includes a connecting rod and corner reflectors welded to the connecting rod. The connecting rod is threadedly connected to the surface of the connecting screw away from the base. The number of corner reflectors is multiple, and the multiple corner reflectors are arranged around the circumference of the connecting rod. The Luneburg sphere base is threadedly connected to one end of the connecting rod away from the connecting screw, and the Luneburg sphere is threadedly connected to the surface of the Luneburg sphere base away from the connecting screw. The wave-transmitting hood covers the Luneburg sphere.

[0012] By adopting the above technical solution, the connecting rod provides an installation position for the corner reflectors and the Luneburg sphere base. The corner reflectors can increase the RCS characteristics of the target missile, facilitating the training of troops.

[0013] Optionally, it further includes plugs. The number of nozzles on the retired rocket is seven, and the number of plugs is three. The three plugs respectively cover three of the nozzles.

[0014] By adopting the above technical solution, the starting thrust of the target missile engine is increased accordingly.

[0015] Optionally, the wave-transmitting hood is a wave-transmitting fiber honeycomb sandwich wave-transmitting hood.

[0016] By adopting the above technical solution, the wave-transmitting hood has the characteristics of light weight and high wave-transmitting rate. The wave-transmitting rate can reach more than 90%, facilitating the training of troops.

[0017] In summary, the present application includes at least one of the following beneficial technical effects: The present application creatively reformed the 122-mm high-speed rocket target missile, realized the safe and reliable launch of the 122-mm high-speed rocket target missile, solved the problem of quickly guaranteeing small targets under actual combat conditions for air defense troops in field conditions. Compared with traditional target missiles, the volume is significantly reduced and the operation is more convenient; This application realizes the functions of simulating infrared characteristics and RCS characteristics on a small high-speed target missile at the same time. Both its infrared characteristics and RCS characteristics can meet the training requirements of corresponding equipment. At the same time, according to the needs of the troops, the range and target supply speed can also be adjusted. Description of the Drawings

[0018] Figure 1 It is a schematic structural diagram of a multi-purpose high-speed target missile based on the restructuring of retired equipment disclosed in the embodiments of this application.

[0019] Figure 2 It is a schematic diagram of a multi-purpose high-speed target missile based on the restructuring of retired equipment in the embodiments of this application.

[0020] Figure 3 It is a schematic diagram aiming to emphasize the connection relationship of the simulated combat cabin, the simulated infrared characteristic module, and the RCS characteristic simulation module.

[0021] Figure 4 It is a schematic structural diagram of the tail stabilizer device.

[0022] Figure 5 It is a schematic diagram of the nozzle.

[0023] Figure 6 It is a schematic diagram of the connecting screw part Figure 7 It is a schematic diagram of the base.

[0024] Figure 8 It is a schematic diagram of the connecting cover.

[0025] Figure 9 It is a test curve of the infrared radiation intensity of the target missile.

[0026] Figure 10 It is a schematic diagram of the Luneburg sphere base.

[0027] Figure 11 It is a schematic diagram of the connecting rod.

[0028] Figure 12 It is a schematic diagram of the corner reflector.

[0029] Figure 13 It is a position relationship diagram of the triangular plates constituting the corner reflector.

[0030] Figure 14 It is a test curve of the RCS characteristics of the target missile.

[0031] Description of reference numerals: 1. Simulated combat cabin; 11. Transparent wave head cover; 2. Front engine; 3. Rear engine; 4. Tail stabilizer mechanism; 5. Nozzle; 6. Simulated infrared characteristic module; 61. Illuminating torch; 62. Base; 63. Connecting cover; 631. Rectangular hole; 64. Ignition cartridge; 65. Automatic ignition part; 7. Connecting screw; 8. RCS characteristic simulation module; 81. Luneburg sphere base; 82. Luneburg sphere; 83. Connecting rod; 84. Corner reflector. Detailed implementation manners

[0032] The following further elaborates on this application in conjunction with the Figure 1 - attached Figure 14 drawings for a more detailed description.

[0033] Currently, for the convenience of troop training, the embodiment of this application proposes a multi-purpose high-speed target missile refitted based on retired equipment. Referring to Figures 1-3 , a multi-purpose high-speed target missile refitted based on retired equipment includes a 122-mm retired rocket shell, a simulated infrared characteristic module 6, a connecting screw 7, and an RCS characteristic simulation module 8. The main body of the retired rocket shell is a retired 122-mm rocket. The retired rocket shell includes a simulated combat cabin 1, a front engine 2 connected to the simulated combat cabin 1, a rear engine 3, a tail stabilizer mechanism 4, and a nozzle 5. The warhead of the original 122-mm rocket is removed from the retired rocket shell and replaced with a simulated combat cabin 1. The simulated combat cabin 1 is located at the front end of the retired rocket shell and provides an installation position for other components.

[0034] The front engine 2 is located between the rear engine 3 and the simulated combat cabin 1, and the rear engine 3 is located between the front engine 2 and the tail stabilizer mechanism 4. The front engine 2, the rear engine 3, the tail stabilizer mechanism 4, and the nozzle 5 can achieve the basic purpose of target missile training. The front engine 2 and the rear engine 3 provide power for the target missile. Both the front engine 2 and the rear engine 3 use the engines of the original 122-mm retired rocket. According to the requirements of the range and flight speed, the charge of the front engine 2 can be removed or retained. The range of the target missile with the charge of the front engine 2 retained can reach 20 km, and the maximum speed can reach 700 m / s, which is suitable for the training of vehicle-mounted air defense missiles; the range of the target missile with the charge of the front engine 2 removed is shortened to 10 km, but its speed drops significantly, and the speed in the target area drops to 220 m / s - 340 m / s, which is convenient for the training of portable air defense missiles for troops.

[0035] Referring to Figure 4 , the tail stabilizer mechanism 4 uses the structure of the original 122-mm retired rocket and is mainly composed of a tail fin frame, four arc-shaped wing surfaces, a pin shaft, and a spring component. Referring to Figure 5, A multi-purpose high-speed target missile based on the refitting of retired equipment also includes a plug. The number of nozzles 5 on the retired rocket is seven, and the number of plugs is three. The three plugs respectively cover three nozzles 5. The nozzles 5 are refitted on the basis of the nozzles 5 of the original 122-mm retired rocket. Three plugs are newly added, changing the original seven nozzles 5 to four nozzles 5, so as to increase the starting thrust of the target missile engine.

[0036] Refer to Figure 2 and Figure 3 , The end of the simulated combat cabin 1 is set as a wave-transparent fiber honeycomb sandwich wave-transparent head cover 11, so that the wave-transparent head cover 11 has the characteristics of light weight and high wave transmission rate, and the wave transmission rate can reach more than 90%. The wave-transparent head cover 11 covers the Luneburg sphere 82, which is convenient for the troops to conduct training. The outer shape of the wave-transparent head cover 11 is processed with reference to the outer shape of the warhead of the original 122-mm retired rocket. The connecting end of the wave-transparent head cover 11 covers the outside of the end of the connecting screw 7. The wave-transparent head cover 11 is fixed to the connecting screw 7 by means of epoxy glue bonding and screw fixation, achieving the purpose of connecting the wave-transparent head cover 11 to the connecting screw 7.

[0037] Through aerodynamic simulation calculation, the overall size of the target missile is increased by about 300 mm on the basis of the original 122-mm retired rocket, and the rest of the outer shape remains unchanged, resulting in a slight decrease in the speed of the target missile. In addition, according to the different types of training ammunition of the troops, the charge of the front engine 2 of the target missile can be selected to be retained or removed, so that the range and target supply speed of the target missile change. In the state of retaining the charge of the front engine 2, the maximum speed of the target missile can reach 700 m / s and the range can reach 20 km, which is convenient for the training of the vehicle-mounted air defense weapon system of the troops; in the state of removing the charge of the front engine 2, the range and flight speed of the target missile are significantly reduced, reaching the subsonic range, which is suitable for the training of the portable air defense missile of the troops.

[0038] Refer to Figure 3 , Figures 6-8 , The simulated infrared characteristic module 6, the connecting screw 7 and the RCS characteristic simulation module 8 are all connected to the inside of the simulated combat cabin 1. The connecting screw 7 is located in the middle of the simulated combat cabin 1, and its outer shape is processed with reference to the outer shape of the warhead of the original 122-mm retired rocket.

[0039] Furthermore, the simulated infrared characteristic module 6 and the RCS characteristic simulation module 8 are both threadedly connected to the connecting screw 7. The simulated infrared characteristic module 6 and the RCS characteristic simulation module 8 are respectively located at both ends of the connecting screw 7, realizing the stable connection of the simulated infrared characteristic module 6 and the RCS characteristic simulation module 8. The simulated infrared characteristic module 6 includes a lighting torch 61 located inside the simulated combat cabin 1. Combined with Figure 8, the flare 61 in the 130mm illumination cartridge selected for the illumination flare 61 has an infrared radiation intensity of up to 1000w / sr, which is used to provide the infrared characteristics of the target missile. At the same time, due to the presence of the simulated light source, the static visible light characteristics of the target missile reach 300000cd, and it can be visually observed and tracked during flight. The RCS characteristic simulation module 8 includes a Luneburg sphere base 81 arranged inside the simulated combat cabin 1 and a Luneburg sphere 82 connected to the Luneburg sphere base 81. The Luneburg sphere 82 is a multi-layered dielectric sphere that can achieve the energy reflection of plane waves and significantly increase the RCS characteristics of the target missile. It is connected to the Luneburg sphere base 81 by means of threads. This application can simulate infrared characteristic targets and RCS characteristic targets at the same time, meeting the training requirements of the troops and facilitating the training of the troops.

[0040] Refer to Figure 3 , Figures 6-8 , the simulated infrared characteristic module 6 is used to enhance the infrared characteristics of the target missile. The simulated infrared characteristic module 6 also includes a base 62 connected to the inner wall of the simulated combat cabin 1, a connecting cover 63 detachably connected to the base 62, an ignition cartridge 64 detachably connected to the base 62, and an automatic ignition part 65 threadedly connected to the connecting screw 7. The base 62 is machined from 45# steel. The flare 61 and the front engine 2 are respectively located at both ends of the base 62. The internal thread at the bottom of the base 62 is B116×2-7H, which is used to dock with the front engine 2 to achieve the purpose of stably threadedly connecting the base 62 to the front engine 2. At the same time, a threaded hole is opened in the middle of the top of the base 62 to achieve the purpose of threadedly connecting the flare 61 to the base 62.

[0041] Refer to Figure 3 , Figures 6-8 , the connecting cover 63 is threadedly connected to the circumferential direction of the end of the base 62 to achieve the purpose of threadedly connecting the connecting cover 63 to the base 62. At the same time, one end of the connecting cover 63 away from the base 62 is threadedly connected to the connecting screw 7 to achieve the stable connection of the connecting screw 7. The connecting cover 63 covers the outside of the flare 61. The connecting cover 63 is machined from 45# steel. A plurality of rectangular holes 631 are opened on the side wall of the connecting cover 63. In the embodiment of this application, the number of the rectangular holes 631 is four. The four rectangular holes 631 are evenly arranged in the circumferential direction of the connecting cover 63, and the size of the rectangular holes 631 is 40mm×60mm. The rectangular holes 631 serve as the radiation window of the flare 61 to achieve the purpose of simulating infrared characteristic targets.

[0042] Refer to Figure 3 , Figures 6-8, the connecting screw 7 is made of 45# steel and is connected to the connecting cover 63 by means of threads. One end of the illuminating torch 61 away from the base 62 is threadedly connected to the connecting screw 7. The ignition cartridge 64 is fixedly connected to the base 62 by screws. The ignition cartridge 64 is pressed against the illuminating torch 61. At the same time, a threaded hole is opened at the bottom of the connecting screw 7 for installing the automatic ignition component 65, so as to achieve the purpose of threadedly connecting the automatic ignition component 65 to the surface of the connecting screw 7 facing the base 62. The automatic ignition component 65 is electrically connected to the ignition cartridge 64. During daily service, there is a short circuit between the automatic ignition component 65 and the ignition cartridge 64. When in use, the automatic ignition component 65 is connected to the ignition cartridge 64 through a plug. Before the target projectile is launched, the automatic ignition component 65 is connected to the ignition cartridge 64. After the launch, it is activated by the launch overload to supply power to the ignition cartridge 64. After the ignition cartridge 64 works, it ignites the illuminating torch 61 to achieve the purpose of simulating the infrared characteristic target.

[0043] Refer to Figures 2-3 , Figure 6 And 10 - Figure 13 , the RCS characteristic simulation module 8 is used to enhance the RCS characteristic of the target projectile. The RCS characteristic simulation module 8 also includes a connecting rod 83 and a corner reflector 84 welded to the connecting rod 83. Both the connecting rod 83 and the Luneburg sphere base 81 are made of 45# steel. The connecting rod 83 is threadedly connected to the surface of the connecting screw 7 away from the base 62. The corner reflector 84 is formed by welding three triangular metal plates and is used to increase the RCS characteristic of the target projectile. The number of corner reflectors 84 is multiple, and multiple corner reflectors 84 are wound around and welded to the circumference of the connecting rod 83. The Luneburg sphere base 81 is threadedly connected to one end of the connecting rod 83 away from the connecting screw 7. The Luneburg sphere 82 is threadedly connected to the surface of the Luneburg sphere base 81 away from the connecting screw 7. The connecting rod 83 provides an installation position for the corner reflector 84 and the Luneburg sphere base 81. The corner reflector 84 can increase the RCS characteristic of the target projectile, which is convenient for the troops to conduct training.

[0044] The implementation principle of a multi-purpose high-speed target projectile based on the refitting of retired equipment in the embodiment of the present application is: combined with Figure 14, the RCS characteristic of the target missile product of this application reaches a maximum of 4 dBsm, and the infrared radiation characteristic reaches a maximum of 2304 w / sr, which can meet the training requirements of various air defense weapon systems of the troops. The automatic ignition part 65 in the simulated combat cabin 1 of the target missile is short-circuited usually. Before the target missile is launched, the automatic ignition part 65 is connected to the ignition cartridge 64 and loaded into the launch gun barrel. After the front engine 2 and the rear engine 3 are ignited, the booster engine works, mainly used to provide the flight kinetic energy of the target missile. At the same time, the automatic ignition part 65 is activated under the action of launch overload and ignites the ignition cartridge 64 after a delay of about 1 s. The ignition cartridge 64 ignites the illumination torch 61, and the illumination torch 61 can work for more than 60 s. Then the target missile realizes stable flight (level flight section) through its own structure, and then descends under the action of gravity (descent section) until it lands. The target missile mainly completes the corresponding tactical exercise requirements in the level flight section and the descent section.

[0045] The above are all the preferred embodiments of this application, and the protection scope of this application is not limited thereby. Therefore, all equivalent changes made according to the structure, shape, and principle of this application shall be covered within the protection scope of this application.

Claims

1. A multi-purpose high-speed target missile modified from retired equipment, comprising a retired rocket shell, the retired rocket shell comprising a simulated combat compartment (1), a front engine (2) connected to the simulated combat compartment (1), a rear engine (3), a tail stabilizing mechanism (4) and a nozzle (5), the simulated combat compartment (1) being located at the front end of the retired rocket shell, the end of the simulated combat compartment (1) being provided with a wave-transmitting head cover (11), the front engine (2) being located between the rear engine (3) and the simulated combat compartment (1), and the rear engine (3) being located between the front engine (2) and the tail stabilizing mechanism (4), characterized in that: A multi-purpose high-speed target missile reconstructed from retired equipment also includes a simulated infrared characteristic module (6) connected to the simulated combat cabin (1), a connecting screw (7) connected to the simulated combat cabin (1), and an RCS characteristic simulation module (8) connected to the simulated combat cabin (1), wherein the connecting screw (7) is located at the middle end of the simulated combat cabin (1), the wave-transmitting head cover (11) is connected to the connecting screw (7), the simulated infrared characteristic module (6) and the RCS characteristic simulation module (8) are both threadedly connected to the connecting screw (7), the simulated infrared characteristic module (6) and the RCS characteristic simulation module (8) are respectively located at two ends of the connecting screw (7), the simulated infrared characteristic module (6) includes a lighting torch (61) located inside the simulated combat cabin (1), and the RCS characteristic simulation module (8) includes a Luneburg sphere base (81) arranged inside the simulated combat cabin (1) and a Luneburg sphere (82) connected to the Luneburg sphere base (81).

2. The multi-purpose high-speed target missile modified from retired equipment according to claim 1, characterized in that: The simulated infrared characteristic module (6) also includes a base (62) connected to the inner wall of the simulated combat compartment (1), a connection cover (63) detachably connected to the base (62), an ignition cartridge (64) detachably connected to the base (62), and an automatic ignition component (65) threadedly connected to the connection screw (7), the base (62) being threadedly connected to the front engine (2), the lighting torch (61) being threadedly connected to the base (62), the lighting torch (61) and the front engine (2) being respectively located at two ends of the base (62), and the lighting torch (61) being threadedly connected to the front engine (2). One end of the torch (61) away from the base (62) is threadedly connected to the connecting screw (7), the connecting cover (63) is threadedly connected to the base (62), the connecting cover (63) is arranged on the lighting torch (61), the ignition box (64) is fixedly connected to the base (62) by screws, the ignition box (64) is pressed against the lighting torch (61), the automatic ignition component (65) is threadedly connected to the side surface of the connecting screw (7) facing the base (62), and the automatic ignition component (65) is electrically connected to the ignition box (64).

3. The multi-purpose high-speed target missile modified from retired equipment according to claim 2, characterized in that: The side wall of the connection cover (63) is provided with a plurality of rectangular holes (631).

4. The multi-purpose high-speed target missile modified from retired equipment according to claim 2, characterized in that: The RCS characteristic simulation module (8) also includes a connecting rod (83) and a corner reflector (84) welded to the connecting rod (83), wherein the connecting rod (83) is threadedly connected to a side surface of the connecting screw (7) away from the base (62), the number of the corner reflectors (84) is multiple, and the multiple corner reflectors (84) are arranged around the circumference of the connecting rod (83), the Luneburg ball base (81) is threadedly connected to one end of the connecting rod (83) away from the connecting screw (7), the Luneburg ball (82) is threadedly connected to a side surface of the Luneburg ball base (81) away from the connecting screw (7), and the wave-transmitting head cover (11) is covered on the Luneburg ball (82).

5. The multi-purpose high-speed target missile modified from retired equipment according to claim 2, characterized in that: It also includes a plug. The number of the nozzles (5) on the retired rocket is seven, and the number of the plugs is three. The three plugs cover the three nozzles (5) respectively.

6. The multi-purpose high-speed target missile modified from retired equipment according to claim 1, characterized in that: The wave-transmitting head cover (11) is a wave-transmitting fiber honeycomb sandwich wave-transmitting head cover (11).

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